Deep space probe lander power supply device suitable for Jinstar, Mars and South China

Abstract

The invention discloses a deep space probe lander power supply device suitable for Jinxing, Mars and South China, relates to the technical field of deep space exploration, and comprises a parachute which is jointly made of a fabric solar energy supply device, a canopy, a structural parachute cord, a conductive parachute cord and the like. The auxiliary power supply device is composed of an air bag, a parachute cord tractor and a conductive parachute cord winder. The device is characterized in that a fabric type solar energy supply device is adopted to replace a traditional canopy material, the photovoltaic power generation function is integrated on the parachute, meanwhile, an auxiliary power supply device is assisted to achieve the effects of electric connection or unfolding of the parachute on the surface of an extraterrestrial celestial body, and the huge surface area of the parachute serves as the effective solar power generation area; therefore, the power generation efficiency of the deep space detector in a low-illumination-intensity extraterrestrial environment is remarkably improved, and the defect that a traditional deep space detector is deficient in electric energy is overcome.

Description

Technical Field

[0001] The present invention relates to the field of deep space exploration, and in particular to a power supply device suitable for deep space probes (landers) on Venus, Mars and Titan. Background Art

[0002] The power supply for traditional spacecraft is usually provided by solar panels, but deep space probes work in the outer solar system far away from the sun or on the surface of extraterrestrial bodies with poor lighting, and face the problem of power shortage. There are usually three solutions: one is to increase the area of ​​​​the solar panels, but according to the formula that light intensity is inversely proportional to the square of the distance, in order to achieve the same power generation capacity in the outer solar system as in low-Earth orbit, the area of ​​​​the solar panels needs to be increased by dozens of times. This method will greatly increase the launch mass of the spacecraft, exceeding the rocket's carrying capacity limit; the second is to use radioisotope thermal batteries (RTGs), which work on the principle of releasing heat through the decay of radioactive elements and then converting it into stable electrical energy through the thermoelectric effect. However, this faces the shortcomings of output power decay due to the consumption of radioactive elements with their half-life over time, extremely low energy conversion efficiency, high cost, and the possibility of radioactive material leakage if the spacecraft fails to launch; the third is to use chemical energy batteries. Its disadvantage is that chemical energy batteries have a very low energy storage density and can only maintain power supply for a few hours. For example, the Huygens probe lost contact 90 minutes after landing on the surface of Titan in 2005 due to battery exhaustion, which limited the probe's ability to carry out further scientific research.

[0003] Extraterrestrial bodies such as Venus, Mars, and Titan are characterized by their presence of atmospheres and low surface sunlight intensity. For example, Venus's surface sunlight intensity, despite being closer to the Sun, is significantly lower due to the thick clouds in its atmosphere, which block and reflect most sunlight. Consequently, the surface sunlight intensity on Venus is only 10-20% of that on Earth, equivalent to dusk on Earth. Solar radiation intensity at Mars' orbit ranges from 491 to 715 W, averaging 43% of that on Earth. At Saturn's nine astronomical units from the Sun, Titan's surface sunlight intensity is only 1.23% of that on Earth. In summary, spacecraft landing on Venus, Mars, and Titan could utilize their atmospheres for aerodynamic deceleration using a combination of a "blunt body aerodynamic shape + parachute." However, the surface sunlight intensity on these bodies is lower than on Earth, and using traditional solar panels for power generation would result in insufficient power.

[0004] The parachutes used by deep space probes (landers) have a vast surface area, with canopies reaching over ten meters in diameter and covering hundreds of square meters. Lander parachutes typically employ a disc-slit configuration, characterized by a small hole in the center of the top panel, circular side panels at the bottom, and a wide gap between the top and side panels. When the canopy is inflated, the slits allow approximately 15% air permeability. This configuration offers excellent stability and low canopy drag, making it suitable for deployment in transonic and supersonic environments with thin air.

[0005] Thin-film solar cells are a new type of photovoltaic technology that can achieve photoelectric conversion with a thickness of only a few microns, one-hundredth the thickness of traditional crystalline silicon solar cells. Their photoelectric conversion efficiency can reach up to 20%. This means that although the power generation efficiency of thin-film solar cells per unit area is slightly lower than that of traditional solar panels, the power generation efficiency per unit mass of thin-film solar material after its surface area is fully expanded can be dozens of times higher than that of traditional solar panels. Because thin-film solar cells are generally highly flexible, some studies have shown that the composite materials can be combined with textile fibers to form ideal textile-based solar energy devices, with potential applications in the future such as powering wearable electronic devices.

[0006] Therefore, thin-film solar cell technology can be combined with parachute technology to prepare a new type of parachute canopy material woven from high-strength fibers and thin-film solar cells. The huge surface area of ​​the parachute can be used to receive solar radiation to make up for the shortcoming of insufficient power generation of deep space probes on the surface of celestial bodies with poor lighting. Summary of the Invention

[0007] The purpose of the present invention is to provide a power supply device for deep space probes (landers) suitable for Venus, Mars and Titan. It can not only solve the problem of power shortage faced by deep space probes operating in the outer solar system far away from the sun or on the surface of extraterrestrial bodies with poor lighting in the existing technology, but also will not increase the launch mass of the deep space probes.

[0008] To achieve the above objectives, the present invention employs the following technical solutions: a power supply device for a deep space probe (lander) suitable for use on Venus, Mars, and Titan, characterized by comprising a probe body, a heat-insulating base, a heat shield, a parachute (including a canopy and lines), and an auxiliary power supply device. The canopy is partially or entirely replaced with a fabric solar-powered device. The total number of lines should be a multiple of 12, with their upper ends connected to the canopy and their lower sections gathered into a line bundle and then fixed to the top of the heat shield, together forming the main structure of the parachute. The auxiliary power supply device consists of a conductive line winder, a line tractor, and an airbag. The line tractor and airbag are integrated into a single unit and mounted on the lines. When the parachute is in the open position, its position is constrained to a certain distance above the line gathering point by the combined effects of gravity and line elasticity. The conductive line winder is fixed inside the heat shield near the line bundle suspension point. When the probe is in the launch, cruise or re-entry state, the probe body and the auxiliary power supply device are protected inside the heat-insulating bottom and the heat-insulating cover. A parachute cover is provided outside the heat-insulating cover, and the parachute is stored inside the parachute cover.

[0009] Furthermore, the parachute specifically refers to the main parachute with the largest canopy area in the lander, and its configuration is a disk-gap-band parachute (DGB) structure, and the parachute ropes can be further divided into structural parachute ropes and conductive parachute ropes.

[0010] Furthermore, the fabric-based solar energy device is woven using a canopy base material comprising a plain weave fabric woven with interlaced warp and weft threads. Furthermore, a portion of the warp threads in the canopy base material is replaced with thin-film solar cells, each of the same width as the warp threads. The thin-film solar cells alternately pass through three weft threads and then through one weft thread throughout the entire length of the base material, forming a three-up, one-down weave pattern. After being separated from the thin-film solar cells by three or more ordinary warp threads, the warp threads are again replaced by thin-film solar cells, following the same weave pattern as above, but with one weave point raised. Furthermore, reinforcing threads are woven into the fabric-based solar energy device at intervals in the weft direction using a double plain weave or a square weave.

[0011] Furthermore, the structural parachute cord is coaxially braided, with an inner core made of ultra-high molecular weight polyethylene (UHMWPE) in a hollow tubular structure. Two layers of aramid fiber, helically braided in different directions, form an outer core, encasing the inner core. The conductive parachute cord is based on the structural parachute cord, but with copper conductors added to the hollow tubular core. The copper conductors are twisted at regular intervals to form knots, while remaining mostly straight.

[0012] Furthermore, the fabric solar energy supply device contains multiple thin-film solar cells, and bus bars are respectively led out from both ends of the thin-film solar cells. The bus bar located at the upper part of the fabric solar energy supply device starts from the top of the rightmost thin-film solar cell in the fabric solar energy supply device, connects to the tops of all thin-film solar cells in the fabric solar energy supply device from right to left, and converges to the copper wire in the conductive parachute on the left; similarly, the bus bar located at the lower part of the fabric solar energy supply device starts from the bottom end of the leftmost thin-film solar cell in the fabric solar energy supply device, connects to the bottoms of all thin-film solar cells in the fabric solar energy supply device from left to right, and converges to the copper wire in the conductive parachute on the right.

[0013] Furthermore, the parachute structure is such that the fabric solar energy device and the canopy are fixed to the structural parachute lines and the conductive parachute lines, respectively. The fabric solar energy device and the canopy can be fixed between each pair of conductive parachute lines, while only the canopy can be fixed between the conductive parachute lines and the structural parachute lines.

[0014] Furthermore, the parachute rope tractor includes a parachute rope tractor body, which is in the shape of a flat hexahedron, with a top surface and a bottom surface being square and a side surface being a narrow and long rectangle. Rotating rods are respectively provided on the four sides of the parachute rope tractor body, and the proximal end of the rotating rod extends to the interior of the parachute rope tractor body and is connected to the motor, while a through hole is opened at the distal end of the rotating rod, and four parachute ropes of the above structure are selected to pass through the through holes respectively; the airbag is installed on the top surface of the parachute rope tractor body in a folded state, a small hole is opened on the wall of the airbag and an air guide tube is led out, and the other end of the air guide tube extends to the micro fan after penetrating the one-way valve and is fixedly connected to the air outlet thereon; the conductive parachute rope winder includes a conductive parachute rope storage cylinder, the conductive The parachute rope storage tube is fixed on the top of the inner side of the heat insulation cover and a conductive parachute rope storage tube core is provided inside the tube. One end of the conductive parachute rope storage tube is closed and the other end is open. A combing ring, an outer guide wheel and an inner guide wheel are provided on the right side of the open end of the conductive parachute rope storage tube from near to far, and the combing ring, outer guide wheel and inner guide wheel are all fixed on the inclined wall surface of the inner side of the heat insulation cover. The conductive parachute rope is wound around the conductive parachute rope storage tube core layer by layer and is stored in the conductive parachute rope storage tube. One end of the conductive parachute rope extends from the closed end of the conductive parachute rope storage tube and passes through the heat insulation cover to the parachute rope bundle hanging point, and is connected to the conductive parachute on the parachute through the parachute rope bundle. The other end passes through the opening of the conductive parachute rope storage tube and is connected to the detector body after passing through the combing ring, the outer guide wheel and the inner guide wheel. Furthermore, grooves are provided on the outer guide wheel and the inner guide wheel, the conductive parachute rope is tangent to the side of the outer guide wheel away from the heat insulation cover and embedded in the groove on the outer guide wheel, and similarly, the conductive parachute rope is tangent to the side of the inner guide wheel close to the heat insulation cover and embedded in the groove on the inner guide wheel, and a tension adjustment spring is provided at the connection between the outer guide wheel and the heat insulation cover.

[0015] Furthermore, the material of the thin film solar cell is selected from one or more mixtures of copper indium gallium selenide solar cells (CIGS), perovskite solar cells (Pe SCs), and polymer solar cells (PSCs).

[0016] Compared with the prior art, the power supply device for deep space probes (landers) suitable for Venus, Mars and Titan provided by the present invention has the following beneficial effects:

[0017] 1. This invention combines parachute technology with thin-film solar cell technology, without significantly increasing the weight per unit area of ​​the parachute canopy fabric or reducing the tensile strength per unit cross-sectional area of ​​the canopy fabric. This results in a fabric-based solar energy device woven from aramid fiber and thin-film solar cells. Parachutes made with this fabric-based solar energy device as a new canopy material are expected to be used to power deep space probes (landers) to Venus, Mars, and Titan, without significantly increasing the weight of the parachute system carried by the probe.

[0018] 2. The present invention adopts fabric solar energy supply devices to replace traditional canopy materials, and uses the huge surface area of ​​the parachute carried by the deep space probe (lander) as the effective solar power generation area, solving the problem of power generation shortage caused by insufficient sunlight on the surface of extraterrestrial bodies, and can provide sufficient electricity for spacecraft.

[0019] 3. In order to adapt to environmental factors such as temperature, light intensity and air pressure on the surfaces of different celestial bodies, the present invention has designed three auxiliary power supply devices: an airbag, a parachute puller and a conductive parachute winder. These three auxiliary power supply devices can connect the textile solar energy supply device with the detector body, spread the parachute on the surface to increase the contact area between the textile solar energy supply device on the parachute and sunlight, and prop up the parachute to prevent dust adhesion, thereby improving the service life and power generation efficiency of the power supply device in the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0021] Figure 2 This is a schematic diagram of the structure of the fabric solar energy supply device in the present invention;

[0022] Figure 3 Schematic diagram of the parachute rope structure in the present invention;

[0023] Figure 4 A schematic cross-sectional view of a conductive parachute cord in the present invention;

[0024] Figure 5 This is a circuit diagram of the single-piece fabric solar energy supply device of the present invention;

[0025] Figure 6 This is a circuit diagram of the fabric solar energy supply device in the parachute of the present invention;

[0026] Figure 7 This is a schematic diagram of the structure of the parachute rope tractor in the present invention;

[0027] Figure 8 Schematic cross-sectional view of the parachute rope puller in the present invention;

[0028] Figure 9 It is a partial cross-sectional diagram of the airbag in the present invention;

[0029] Figure 10 Schematic diagram of a half-section of the conductive parachute cord winder of the present invention;

[0030] Figure 11 This is an implementation effect diagram of Example 1 of the present invention;

[0031] Figure 12 This is an implementation effect diagram of Example 2 of the present invention;

[0032] Figure 13 This is an implementation effect diagram of Example 3 of the present invention;

[0033] Figure 14 This is a working principle diagram of the parachute rope puller in Example 2 and Example 3 of the present invention;

[0034] Figure 15 This is a schematic diagram of the tensile strength test principle of the fabric solar energy device in the present invention;

[0035] Among them: 1. Detector body; 2. Parachute; 21. Fabric solar energy device; 211. Weft; 212. Warp; 213. Reinforcement thread; 22. Canopy; 23. Parachute cord; 231. Structural parachute cord; 232. Conductive parachute cord; 233. Parachute cord inner core; 234. Parachute cord outer core; 235. Copper wire; 236. Wire knot; 237. Parachute cord bundle; 3. Auxiliary power supply device; 31. Airbag; 311. One-way valve; 312. Micro fan; 313 , air guide tube; 32, parachute rope tractor; 321, parachute rope tractor body; 322, rotating rod; 323, through hole; 324, motor; 33, conductive parachute rope winder; 331, conductive parachute rope storage tube; 332, conductive parachute rope storage tube core; 333, combing ring; 334, outer guide wheel; 335, inner guide wheel; 336, tension adjustment spring; 4, thin-film solar cell; 41, bus bar; 51, thermal insulation outsole; 52, thermal insulation cover; 53, parachute compartment cover. DETAILED DESCRIPTION

[0036] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0037] In the description of the invention, it should be noted that the terms "vertical", "up", "down", "horizontal", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings. They are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, they cannot be understood as limiting the invention.

[0038] In the description of the present invention, it should also be noted that, unless otherwise expressly specified or limited, the terms "disposed," "installed," "connected," and "connected" should be understood in a broad sense. For example, they may refer to fixed connections, detachable connections, or integral connections; they may refer to mechanical connections, connections via pipes, or electrical connections; they may refer to direct connections, indirect connections via an intermediate medium, or internal connections between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0039] Please refer to Figure 1 A power supply device for deep space probes (landers) suitable for Venus, Mars and Titan is characterized by: including a probe body 1, a heat-insulating base 51, a heat-insulating cover 52, a parachute 2 (including a canopy 22 and parachute ropes 23) and an auxiliary power supply device 3. Part or all of the canopy 22 is replaced by a fabric solar energy supply device 21. The total number of parachute ropes 23 should be a multiple of "twelve". The upper ends of the parachute ropes are connected to the canopy 22, and the lower sections are gathered into parachute rope bundles 237 and fixed to the top of the heat-insulating cover 52, together forming the main structure of the parachute 2. The auxiliary power supply device 3 consists of a conductive parachute cord winder 33, a parachute cord tractor 32, and an airbag 31. The cord tractor 32 and airbag 31 are integrated into a single unit and mounted on the parachute cords 23. When the parachute 2 is deployed, gravity and the elastic force of the parachute cords 23 constrain its position to a certain distance above the cord retraction point. The conductive parachute cord winder 33 is fixed inside the heat shield 52 near the suspension point of the parachute cord bundle 237. When the probe is in launch, cruise, or reentry mode, the probe body 1 and the auxiliary power supply device 3 are protected within the heat-insulating base 51 and heat shield 52. A parachute compartment cover 53 is located outside the heat shield 52, and the parachute 2 is stored within the compartment cover 53.

[0040] Furthermore, parachute 2 specifically refers to the main parachute, which has the largest canopy area (22) in the lander. It is a disk-gap-band (DGB) structure, with the parachute lines (23) further divided into structural lines (231) and conductive lines (232). The DGB structure is characterized by a disk-shaped top with a central aperture, which primarily bears the brunt of airflow resistance. The aperture, designed based on aerodynamic characteristics, channels airflow and prevents violent oscillation during high-speed deployment. The annular band, which accounts for 15–20% of the parachute's total height, distributes stress and prevents tearing of the canopy (22). The annular gap between the disk and band allows for partial gas escape, preventing abnormal flipping or wrinkling of the parachute during deployment. The DGB structure was chosen for parachute 2 because it is suitable for deployment at supersonic speeds and low dynamic pressures. Its high strength and tear resistance make it suitable for the extreme operating environments encountered by deep space probe landers during deployment on extraterrestrial bodies such as Mars.

[0041] Please refer to Figure 2 The textile solar energy device 21 is woven using a base material comprising warp threads 212 and weft threads 211 interwoven to form a plain weave. Furthermore, some of the warp threads 212 in the base material are replaced with thin-film solar cells 4, each of equal width to the warp threads 212. The thin-film solar cells 4 alternately pass over three weft threads 211 and then under one weft thread 211 throughout the entire length of the base material, forming a three-over-one-under weave pattern. After the thin-film solar cells 4 have been separated by three or more conventional warp threads 212, the warp threads 212 can be replaced again with thin-film solar cells 4. The weave pattern of the thin-film solar cells 4 is now the same as described above, but with one weave point raised. Furthermore, reinforcing threads 213 are woven into the textile solar energy device 21 at intervals in the weft direction using a double plain weave or a basket weave. It is worth noting that the reinforcement line 213 needs to be sewn every multiple of "two" weft threads, and the sewing position should be staggered with the thin-film solar cell 4 to avoid the reinforcement line 213 penetrating the thin-film solar cell 4 during the sewing process, causing the circuit to be broken and unable to generate electricity.

[0042] On this basis, the canopy 22 also adopts the method of plain weaving with warp 212 and weft 211 one above and one below. The difference from the fabric solar energy supply device 21 is that the canopy 22 does not include the reinforcement line 213 and the thin-film solar cell sheet 4.

[0043] The reason why the base material of the canopy 22 and the fabric solar energy supply device 21 adopts a one-up-one-down plain weave is that the air permeability of this type of fabric is the lowest among all types of plain weaves, making it an ideal material for making the parachute canopy 22; and the thin-film solar cell 4 adopts a three-up-one-down weaving pattern. On the one hand, it is to reduce the obstruction of the weft thread 211 on the thin-film solar cell 4 as much as possible and improve the power generation efficiency. On the other hand, with the thin-film solar cell 4 as a reference, it can be regarded as a twill weave, which has better anti-snagging performance, anti-wrinkle performance and tear strength than the one-up-one-down plain weave; the purpose of adding reinforcement wires 213 in the weft direction is to form a grid structure together with the thin-film solar cell 4 in the warp direction, so as to further improve the tear resistance of the fabric solar energy supply device 21, and prevent the canopy 22 from being torn when the parachute is opened in high-speed airflow.

[0044] Please refer to Figure 3The structural parachute cord 231 is made of coaxial braiding, with an inner core 233 made of ultra-high molecular weight polyethylene in a hollow tubular structure. The outer core 234 is made of two layers of aramid fiber woven in different directions, and the inner core 233 is wrapped around the inner core 234. The conductive parachute cord 232 is based on the structural parachute cord 231, with copper wires 235 added to the hollow tubular structure of the inner core 233. The copper wire 235 is twisted at intervals to form wire knots 236, and most of the rest of the area is in a straight state. Figure 4 shown.

[0045] The reason why the parachute cord 23 adopts the coaxial braiding of the parachute cord inner core 233 and the parachute cord outer core 234 is that the parachute cord inner core 233 with a hollow tube structure has high axial tensile strength and radial torsional resistance; and the parachute cord outer core 234 with a bidirectional spiral braiding has relatively excellent flexibility. Therefore, the coaxial braiding has both tensile performance and flexibility, which can effectively prevent the parachute cord 23 from being broken by its axial tension or radial shear force when the parachute is opened. The inner core of the parachute cord 23 is made of ultra-high molecular weight polyethylene because, in addition to its high tensile strength, it has a relatively smooth surface and a certain degree of lubricity. Under the condition of a large load at the moment of parachute opening, the copper wires 235 in the conductive parachute cord 232 slide against each other in the inner core 233 of the parachute cord, absorbing energy and thus not easily broken. The wire knots 236 formed by winding the copper wires 235 at regular intervals work in the same way as above, giving them a certain degree of elasticity and preventing the copper wires 235 from being broken. The outer core 234 of the parachute cord is made of aramid because aramid material has excellent mechanical properties and can withstand high temperatures of 500°C. It can withstand the heat generated by the aerodynamic heat during parachute opening and the friction between the aramid fibers, so that the tensile strength of the parachute cord 233 will not fail due to high temperature.

[0046] Please refer to Figure 5 The fabric solar energy supply device 21 contains multiple thin-film solar cells 4, and bus bars 41 are respectively extended from both ends of the thin-film solar cells 4. The bus bar 41 located at the upper part of the fabric solar energy supply device 21 starts from the top of the rightmost thin-film solar cell 4 in the fabric solar energy supply device 21, connects to the tops of all the thin-film solar cells 4 in the fabric solar energy supply device 21 from right to left, and converges to the copper wire 235 in the conductive parachute 232 on the left; similarly, the bus bar 41 located at the lower part of the fabric solar energy supply device 21 starts from the bottom end of the leftmost thin-film solar cell 4 in the fabric solar energy supply device 21, connects to the bottoms of all the thin-film solar cells 4 in the fabric solar energy supply device 21 from left to right, and converges to the copper wire 235 in the conductive parachute 232 on the right.

[0047] Please refer to Figure 6The structure of the parachute 2 is as follows: the fabric solar energy device 21 and the canopy 22 are respectively fixed to the structural parachute lines 231 and the conductive parachute lines 232. The fabric solar energy device 21 and the canopy 22 can be fixed between each pair of conductive parachute lines 232, while only the canopy 22 is fixed between the conductive parachute lines 232 and the structural parachute lines 232.

[0048] The circuit principle is as follows: Figure 5 As shown, the upper end of the thin-film solar cell 4 is the positive electrode, and the lower end is the negative electrode. Two bus bars 41 are provided above and below the thin-film solar cell 4. The bus bars 41 respectively connect the positive electrode and the negative electrode of the thin-film solar cell 4 on the single textile solar energy supply device 21, forming a parallel circuit of multiple thin-film solar cells 4. The positive bus bar 41 at the upper end of the thin-film solar cell 4 and the negative bus bar 41 at the lower end of the thin-film solar cell 4 are respectively connected to the copper wires 235 in different conductive parachute ropes 232. Similarly, if Figure 6 As shown, multiple textile solar energy devices 21 are connected in parallel to two conductive parachute cords 232. The conductive parachute cord 232 on the left side of the textile solar energy device 21 serves as the positive electrode, while the conductive parachute cord 232 on the right side of the textile solar energy device 21 serves as the negative electrode. Finally, all conductive parachute cords 232 on the parachute 2 are gathered into a cord bundle 237. All positive conductive parachute cords 232 are combined to form a total positive power supply. Similarly, the total negative power supply is composed of multiple negative conductive parachute cords 232, forming a parallel circuit comprising multiple pairs of positive and negative conductive parachute cords 232.

[0049] It's worth noting that the power supply device in this invention, comprised of three parallel-connected thin-film solar cells (4), provides DC power with high current and low voltage characteristics. This makes it difficult to directly power the payload on the probe, requiring additional energy storage and voltage conversion equipment. Furthermore, since voltage conversion circuits are commonly used and represent mature technology, their electrical connections and specific circuit structure will not be detailed here.

[0050] Please refer to Figure 7-8 The parachute rope puller 32 includes a parachute rope puller body 321. The parachute rope puller body 321 is in the shape of a flat hexahedron, with a square top and bottom and a narrow rectangular side. Rotating rods 322 are respectively provided on the four sides of the parachute rope puller body 321. The proximal end of the rotating rod 322 extends to the interior of the parachute rope puller body 321 and is connected to the motor 324. The rotating rod 322 has a through hole 323 at the distal end. Four parachute ropes 231 of the above structure are selected to pass through the through holes 323 respectively. Figure 9As shown, the airbag 31 is folded and mounted on the top surface of the parachute rope tractor body 321. A small hole is opened on the wall of the airbag 31 and an air guide tube 313 is led out. The other end of the air guide tube 313 extends to the micro fan 312 after penetrating the one-way valve 311 and is fixedly connected to the air outlet thereon; the conductive parachute rope winder 33 includes a conductive parachute rope storage cylinder 331, which is fixed to the top of the inner side of the heat insulation cover 52 and has a conductive parachute rope storage cylinder core 332 inside. One end of the conductive parachute rope storage cylinder 331 is closed and the other end is open. On the right side of the open end of the conductive parachute rope storage cylinder 331, a combing ring 333, an outer guide wheel 334 and The inner guide wheel 335, and the combing ring 333, the outer guide wheel 334, and the inner guide wheel 335 are all fixed on the inner inclined wall of the heat insulation cover 52. The conductive parachute rope 232 is wound layer by layer on the conductive parachute rope storage tube core 332 and is stored in the conductive parachute rope storage tube 331. One end of the conductive parachute rope extends from the closed end of the conductive parachute rope storage tube 331 and passes through the heat insulation cover 52 to the parachute rope bundle 237 suspension point, and is connected to the conductive parachute rope 232 on the parachute 2 through the parachute rope bundle 237. The other end passes through the opening of the conductive parachute rope storage tube 331 and is connected to the detector body 1 after passing through the combing ring 333, the outer guide wheel 334 and the inner guide wheel 335. See for details. Figure 10 Furthermore, grooves are formed on the outer guide wheel 334 and the inner guide wheel 335. The conductive parachute cord 232 is tangent to the side of the outer guide wheel 334 away from the heat shield 52 and is embedded in the groove of the outer guide wheel 334. Similarly, the conductive parachute cord 232 is tangent to the side of the inner guide wheel 335 close to the heat shield 52 and is embedded in the groove of the inner guide wheel 335. A tension adjustment spring 336 is provided at the connection between the outer guide wheel 334 and the heat shield 52.

[0051] The working principle of the parachute rope tractor 32 is: when the probe lands successfully and the main parachute falls over, one side of the parachute 2 will be pressed under the other side, which means that half of the area of ​​the main parachute cannot be directly exposed to sunlight, and the power generation efficiency is low. Since there are four structural parachute lines 231 that pass through the through holes 323 on the rotating rod 322 respectively, the top one of the structural parachute lines 231 (the side where the main parachute is not covered) is selected, and the motor 324 inside the parachute line tractor 32 for controlling the above-mentioned structural parachute lines 231 is started. The structural parachute lines 231 are wound around the rotating rod 322 and the length of the structural parachute lines 231 is shortened, and the connection point between the structural parachute lines 231 and the canopy 22 is dragged toward the direction of the detector body 2, and the nearby parachute lines 23 and canopy 22 are also driven to move toward the direction of the detector body 1. At the same time, the parachute lines 23 that are covered under the parachute and close to the ground are kept stationary under the dual effects of friction and inertia, which plays a role in fixing the position of the parachute 2, and finally causes the main parachute to be spread out on the surface, solving the problem that half of the area of ​​the parachute 2 cannot be directly exposed to sunlight, thereby increasing the power generation.

[0052] The reason for using structural parachute cords 231 through through-holes 323 in the parachute cord puller 32 is that when the motor 324 is activated and the parachute cords 23 are wound around the rotating rod 322, the conductive parachute cords 232 contain copper conductors 235. This could cause the copper conductors 235 to break due to the varying radial curvature radii of the conductive parachute cords 232 during winding, leading to a short circuit. The absence of copper conductors within structural parachute cords 231 effectively avoids this problem. Furthermore, if conductive parachute cords 232 were used in place of structural parachute cords 231, electromagnetic interference would occur when the conductive parachute cords 232 are wound around the rotating rod 322 and current flows through them, affecting both the current and voltage of the textile solar energy device 21.

[0053] The working principle of the conductive parachute cord winder 33 is: when the parachute 2-heat insulation cover 52 is separated from the detector body 1, the conductive parachute cord 232 stored in the conductive parachute cord storage tube 331 is released from the opening on the right side of the conductive parachute cord storage tube 331, and the conductive parachute cord 232 falls off in a circular shape (or spiral shape) around the core 332 of the conductive parachute cord storage tube. The function of the combing ring 333 is to comb the circularly shed conductive parachute cord 232 into a straight line to prevent the conductive parachute cord 232 from getting knotted. On the right side of the combing ring 333, the conductive parachute cord 232 is tightened between the outer guide wheel 334 and the inner guide wheel 335, wherein the outer guide wheel 334 and the inner guide wheel 335 control the pay-out speed of the conductive parachute cord 232 and facilitate adjustment of the pay-out direction of the conductive parachute cord 232. The tension adjustment spring 336 under the outer guide wheel 334 can adjust the tension applied to the section of the conductive parachute cord 232 between the combing ring 333 and the inner guide wheel 335 by allowing the outer guide wheel 334 to have a certain degree of freedom in the direction toward or away from the heat insulation cover 52, so as to prevent the conductive parachute cord 232 from being broken. The above-mentioned "convenient adjustment of the pay-out direction of the conductive parachute rope 232" specifically means that after the parachute 2-heat shield 52 is separated from the detector body 1, the relative speed of the two movements is very large, but with the parachute 2-heat shield 52 as the reference system, the angular velocity of the detector body 1 and the parachute 2-heat shield 52 is not high. Therefore, an inner guide wheel 335 with a structure similar to a pulley is used as the end of the conductive parachute rope winder 33 in contact with the conductive parachute rope 232. It is suitable for working conditions where the angular velocity of the pay-out direction of the conductive parachute rope 232 does not change much, making the pay-out process smoother and effectively avoiding the conductive parachute rope 232 from being broken.

[0054] The working principle of the airbag 31 is as follows: when the probe successfully lands and the main parachute collapses, the micro-blower 312 turns on, pumping the atmosphere of the landed extraterrestrial body through the air duct 313, through the one-way valve 311, and into the folded airbag 31. The airbag 31 gradually inflates and unfolds. Because the parachute line puller 32 is fixed within the area bounded by the parachute lines 23 and the canopy 22, and the airbag 31 is fixed to the top of the parachute line puller 32, the airbag 31 is also constrained between the parachute lines 23 and the canopy 22 after inflation, thereby propping up the canopy 22. When the airbag 31 is fully inflated, the micro-blower 312 turns off. Because the one-way valve 311 is present, the gas in the airbag 31 cannot flow back into the atmosphere through the air duct 313. Therefore, after the initial inflation, the airbag 31 can remain fully inflated for a long time without requiring further inflation.

[0055] Furthermore, the material of the thin film solar cell 4 is selected from one or a mixture of copper indium gallium selenide solar cells (CIGS), perovskite solar cells (Pe SCs), and polymer solar cells (PSCs). Specific embodiment 1:

[0057] This scheme describes the application of the present invention to the atmosphere of Venus, which is primarily composed of carbon dioxide, with small amounts of nitrogen and trace amounts of sulfur dioxide. The surface environment on Venus is characterized by high temperature and pressure, with an average surface temperature of 462°C and a pressure of 90 atmospheres. The upper atmosphere, on the other hand, is relatively mild, with a pressure of only one standard atmosphere and a temperature of 30°C at an altitude of 50 km. The probe deployed its parachute in the upper atmosphere of Venus, at an altitude between 50 and 65 km, at a speed of approximately Mach 0.3, a subsonic deployment condition.

[0058] In this embodiment, the probe body 1 is designed to be integrated with the heat-insulating base 51 and the heat-insulating cover 52. That is, the heat-insulating base 51 and the heat-insulating cover 52 are not separated during the landing process, and the probe does not carry the auxiliary power supply device 3. The parachute size is four meters in diameter, and the rest of the structure is consistent with the content of the invention. The reason why the probe adopts an integrated design with the heat-insulating base 51 and the heat-insulating cover 52 is that the surface of Venus is high temperature and high pressure. Retaining the heat-insulating base 51 and the heat-insulating cover 52 can act as a heat-insulating material to keep the probe warm and also serve as a pressure-resistant shell. Because the atmosphere of Venus is dense, the terminal velocity of the probe is low when it lands, and there is no need to use landing legs to cushion the landing, so there is no need to abandon the heat-insulating base 51. The material of the thin-film solar cell 4 is copper indium gallium selenide (CIGS) because perovskites (Pe SCs) and polymer solar cells (PSCs) are not resistant to high temperatures and are prone to failure in the environment on the surface of Venus.

[0059] The implementation process of the present invention in specific embodiment 1 is as follows Figure 11 As shown:

[0060] a. The lander enters the upper atmosphere of Venus at orbital speed, where its blunt-body aerodynamic shape rubs against the atmosphere to slow it down until it reaches subsonic speed.

[0061] b. The lander pops out the parachute canopy 53 and pulls out the guide parachute;

[0062] c. The pilot parachute pulls out the main parachute (i.e. main parachute 2);

[0063] d. The main parachute is in the drawstring state and is full;

[0064] e. The main parachute is released from the restraint state and is fully inflated;

[0065] f. The lander touches the surface of Venus and the main parachute collapses;

[0066] g. The organic material in the textile solar energy device 21 is pyrolyzed in the high temperature environment on the surface of Venus, and the thin-film solar cell 4 in the main parachute is exposed to the surface of Venus, so as to minimize the obstruction of the thin-film solar cell due to the overlap or wrinkles of the parachute, thereby improving the power generation efficiency. Specific embodiment 2

[0068] This solution applies the present invention to the Martian atmosphere. The Martian atmosphere is primarily composed of approximately 96% carbon dioxide, with trace amounts of nitrogen and argon. The surface atmospheric pressure is only 0.6% of Earth's. The probe deploys its parachute at an altitude of 10-15 km above the Martian surface, at a speed of approximately Mach 2, a supersonic deployment. Furthermore, dust storms are frequent on the Martian surface, necessitating dust protection for solar components.

[0069] In this embodiment, all structures are identical to those described in the disclosure. For example, the auxiliary power supply 3 comprises an airbag 31, a parachute cord puller 32, and a conductive parachute cord winder 33. The probe body 1, heat shield 52, and heat-insulating base 51 are designed separately. The parachute 3 has a diameter of 20 meters and a canopy area of ​​200-300 square meters.

[0070] The implementation process of the present invention in specific embodiment 2 is as follows Figure 12 As shown:

[0071] a. The lander enters the upper atmosphere of Mars at orbital velocity. Its blunt-body aerodynamic shape decelerates due to friction with the atmosphere. Due to the thin atmosphere of Mars, the terminal velocity that the lander can reach through aerodynamic deceleration is approximately Mach 2.

[0072] b. The lander pops out the parachute canopy 53 and pulls out the guide parachute;

[0073] c. The guide parachute pulls out the drag parachute;

[0074] d. The parachute is in the drawbar state and is fully filled;

[0075] e. The drag parachute is released from its restraint state and is fully inflated;

[0076] f. The drag parachute pulls out the main parachute (i.e. main parachute 2) and then separates;

[0077] g. The main parachute is in the drawstring state and is full;

[0078] h. The main parachute is released from the restraint state and is fully inflated;

[0079] i. Heat-insulating outsole 51;

[0080] j. The detector body 1 is separated from the heat shield 52, and the reverse thrust engine is ignited. Simultaneously, the conductive parachute cord winder 33 in the auxiliary power supply device 3 is activated and the conductive parachute cord 232 is released. After the detector body 1 is separated from the main parachute-heat shield 52, it is still connected via the conductive parachute cord 232.

[0081] k. The probe body 1 contacts the Martian surface, the thrust reverser engine shuts down, and the main parachute and heat shield 52 assembly falls tens to hundreds of meters away from the probe body, with the main parachute falling over.

[0082] 1. The airbag 31 and the parachute cord tractor 32 in the auxiliary power supply device 3 are activated. First, the parachute cord tractor 32 retracts the structural parachute cords 231 located on the upper part of the main parachute to spread the main parachute as much as possible on the Martian surface. Then, the airbag 31 begins to inflate, propping up the main parachute and leaving the Martian surface. Finally, power is transmitted to the probe body through the conductive parachute cords 232 between the probe body and the main parachute-heat shield 52.

[0083] The conductive parachute cord reel 33 in this embodiment serves the purpose of ensuring that, due to the thin atmosphere on the Martian surface, the terminal velocity of the probe body 1 remains high even with parachute 2 in place, requiring the ignition of the reverse thrust engine on the probe body 1 to achieve a soft landing. During this ignition process, for safety and weight reduction reasons, the probe body 1 will separate from the parachute 2 and heat shield 52. The conductive parachute cord reel 33 serves to connect the probe body 1 and parachute 2 via a wire (i.e., conductive parachute cord 232) throughout the separation and landing process. After a successful landing, the electrical energy generated by the textile solar energy device 21 on parachute 2 can be transferred to the probe body 1 to provide power.

[0084] The main parachute is held up by the combined action of the airbag 31 and the parachute rope tractor 32, which not only increases the contact area between the fabric solar energy supply device 21 on the main parachute and sunlight, but also prevents dust from adhering to the surface of the main parachute. This improves the power generation efficiency and also extends the service life of the present invention in a dusty environment. Specific embodiment 3

[0086] This embodiment illustrates the application of the present invention to the atmosphere of Titan's surface. Titan's atmosphere is composed of 98% nitrogen and 1.5% methane, with an average surface temperature of -179°C and a pressure of 1.5 atmospheres. The stratosphere reaches a temperature of -98°C due to a temperature inversion phenomenon. The probe deployed its parachute in Titan's stratosphere at a speed of approximately Mach 0.5, a subsonic deployment condition.

[0087] The probe adopts an integrated design with a heat shield 52. During landing, the heat shield 52, located on top of the probe body 1, remains intact; only the heat shield 53 is discarded. The probe's auxiliary power supply unit 3 only carries the parachute cord tractor 32, not the airbag 31 or the parachute cord winder 33. The remaining structure is consistent with the invention, and the parachute size is 8-10 meters in diameter. The probe body 1 and heat shield 52 are designed to be integrated because Titan's surface is cold, and retaining the heat shield 51 and heat shield 52 can serve as thermal insulation to keep the probe body 1 warm. However, compared to Venus, Titan's terminal velocity is higher upon landing, and Titan's surface is characterized by its rugged, pebbled terrain formed by water ice. Therefore, the heat shield 51 must be discarded and the landing legs extended to cushion the landing and prevent the probe from rolling. The thin-film solar cells 4 are made of copper indium gallium selenide (CIGS) because of its high carrier mobility and minimal electrical degradation when the temperature drops, making it more suitable for extremely low-temperature environments.

[0088] The implementation process of the present invention in specific embodiment 3 is as follows Figure 13 As shown:

[0089] a. The lander enters Titan's upper atmosphere at orbital speed, where its blunt-body aerodynamic shape rubs against the atmosphere to slow it down until it reaches transonic speed.

[0090] b. The lander pops out the parachute canopy 53 and pulls out the drag parachute;

[0091] c. The parachute is in the drawbar position;

[0092] d. The drag parachute is released from its restraint state and is fully inflated;

[0093] e. The drag parachute pulls out the main parachute (i.e., main parachute 2), and then separates. At this time, the main parachute is in the drawbar state;

[0094] f. The main parachute is released from the restraint state and is fully inflated;

[0095] g. The heat-insulating outsole 51 is thrown away. The heat shield 52 and the lander are designed to be integrated. They can keep the electronic equipment inside the probe warm under the ultra-low temperature environment on the surface of Titan. Therefore, they are not separated.

[0096] h. The lander touches the surface of Titan and the main parachute collapses;

[0097] i. The auxiliary power supply device 3 (parachute rope tractor 32) is activated to retract the parachute rope 23 located on the upper part of the main parachute, spreading the main parachute as much as possible on the surface of Titan, and increasing the contact area between the textile solar energy supply device 21 on the main parachute and sunlight.

[0098] The specific working principle of the parachute rope tractor 32 is as follows Figure 14 As described above, the parachute in this embodiment has a total of twelve parachute cords 23, which are named a1 in clockwise direction, among which a, d, g and j are structural parachute cords 231, and the remaining eight are conductive parachute cords 232. The four rotating rods 322 on the parachute cord puller 32 are named wz in clockwise direction, among which the structural parachute cord 231 with sequence number a passes through the through hole 323 on the rotating rod 322 with sequence number w. Similarly, the structural parachute cord 231 with sequence number j passes through the through hole 323 on the rotating rod 322 with sequence number x; the structural parachute cord 231 with sequence number g passes through the through hole 323 on the rotating rod 322 with sequence number y; and the structural parachute cord 231 with sequence number d passes through the through hole 323 on the rotating rod 322 with sequence number z. When the lander touched the surface of Titan and the main parachute (i.e., parachute 2) fell over, one side of the main parachute was pressed under the other side, that is, the seven parachute lines 23 numbered ad, jl were pressed under the five parachute lines 23 numbered ei, which means that half of the area of ​​the main parachute cannot be directly exposed to sunlight, and the power generation efficiency is low. Among them, the structural parachute rope 231 with serial number a is located at the top of the parachute 2 (the side of the main parachute away from the ground). At this time, the motor 324 connected to the rotating rod 322 with serial number w on the parachute rope tractor 32 is started, and the structural parachute rope 231 with serial number a is wound around the rotating rod 322 with serial number w and its length is shortened, dragging the connection point between the structural parachute rope 231 with serial number a and the canopy 22 toward the direction close to the detector body 1, and driving the nearby parachute ropes 23 (such as the conductive parachute ropes 232 with serial numbers b and l) to also approach the direction of the detector body 1. At the same time, the parachute rope 23 with serial number ei close to the ground does not move under the dual action of friction and inertia, which eventually causes the parachute 2 to spread out on the surface, and the power generation is increased by increasing the contact area between the fabric solar energy supply device 21 on the parachute 2 and the sunlight.

[0099] In order to simulate the implementation effect of the present invention on the surfaces of Venus, Mars and Titan, the performance of the fabric solar energy supply device 21 (or parachute cord 23 samples) in specific embodiments 1-3 was tested.

[0100] (1) Surface density test

[0101] Surface density is the mass per unit area of ​​fabric. According to the national standard GB / T 4669-2008 "Textiles. Woven fabrics. Determination of mass per unit length and mass per unit area", the surface density test was carried out on the textile solar energy device 21 and the umbrella canopy 22. The specific method is as follows: 3-5 samples of the textile solar energy device 21 and the umbrella canopy 22 with an area of ​​10cm×10cm were taken, and the weight of each sample was measured with a precision balance. The surface density (g / m2) was calculated using the following formula. 2 ) = sample mass (g) / sample area (m 2 ) Calculate the mass per unit area of ​​each sample and take the average value as the result.

[0102] Table 1 Fabric solar energy supply devices and umbrella canopy surface density

[0103] Sample name <![CDATA[Areal density (g / m 2 )]]> Fabric solar energy devices 80.27 umbrella canopy 76.51

[0104] As shown in Table 1, compared to the base material of the canopy 22, the surface density of the fabric solar energy device 21 increased by only 4.9% after replacing the warp threads 212 with thin-film solar cells 4 and adding reinforcement threads 213. This indicates that, in the present invention, replacing part of the canopy 22 fabric with the fabric solar energy device 21 does not significantly increase the total weight of the parachute 2, nor does it increase the launch mass of the deep space probe.

[0105] (2) Mechanical properties test

[0106] The tensile strength test method for textile solar energy devices 21 can be conducted in accordance with the national standard GB / T3923.1-2013, "Tensile properties of textile fabrics - Part 1: Determination of breaking strength and elongation (Strip method)." The specific procedure is as follows: Specimen preparation requires cutting strips measuring 300 mm x 50 mm along the warp and weft directions. The tensile speed is set at 50 mm / min, and the pre-tension is 0.5% of the estimated tensile strength of the specimen. A mechanical clamp is used during the test, maintaining a constant clamping pressure (≥70 kPa) to prevent specimen slippage.

[0107] Since the fabric solar energy device 21 is anisotropic, it is necessary to measure its tensile strength horizontally to the reinforcement line (i.e. perpendicular to the thin film solar cell 4) and perpendicular to the reinforcement line (i.e. parallel to the thin film solar cell 4), as shown in the following example: Figure 15 The experiment was repeated five times in each direction and the average value was taken.

[0108] The tensile strength σ is calculated using the following formula b :

[0109] σ b =F b / S0

[0110] Where: F b is the maximum force that the fabric can withstand when it breaks (in Newtons, N); S0 is the original cross-sectional area of ​​the fabric (in square meters, m 2 ).

[0111] Table 2 Tensile strength of textile solar energy devices and control examples in different directions

[0112] Sample name Tensile strength (MPa) Fabric solar energy device (horizontal to the reinforcement line) 1780.45 Fabric solar energy device (perpendicular to the reinforcement line) 2012.48 umbrella canopy 1856.22

[0113] Testing the tensile strength of paracord 23 should be conducted in accordance with the national standard GB / T 8834-2016, "Fiber Ropes - Determination of Tensile Strength." The specific steps are as follows: Cut a sample of paracord 23 ≥ 0.1 m in length and secure both ends with heat seals or bar knots as required to prevent unraveling. Before testing, equilibrate the sample in a standard environment (temperature 20 ± 2°C, humidity 65% ​​± 4%) for 24 hours to eliminate the effects of temperature and humidity. Secure both ends of the sample in the preloaded clamps of a universal testing machine, ensuring a clamping distance of ≥ 100 mm to prevent slippage. Set the tensile speed to 300 ± 10 mm / min, start the machine, and stretch uniformly until breaking. Record the maximum breaking force (kN). Repeat the test five times, taking the average of the maximum breaking forces and calculating the tensile strength using the formula above. It is worth noting that in addition to testing paracord 23's derivative configurations, paracord 231 and conductive paracord 232, this experiment also tested a rope made of pure aramid fiber as a control.

[0114] Table 3 Tensile strength of structural parachute rope, conductive parachute rope and control example

[0115] Sample name Tensile strength (MPa) Structural paracord 1753.80 Conductive paracord 1756.43 Control Example 2815.84

[0116] From Table 2 and Table 3, it can be seen that compared with the canopy 22 base material made of plain weave aramid material, the textile solar energy supply device 21 has a slightly lower tensile strength in the direction horizontal to the reinforcement line 213, which is 4.1% lower than the canopy 22 base material. This is because after the warp 212 is replaced by the thin-film solar cell 4, the material tensile strength of the thin-film solar cell 4 is lower than that of the aramid fiber; while the tensile strength of the textile solar energy supply device 21 in the direction perpendicular to the reinforcement line 213 is higher than that of the canopy 22 base material, which is 8.4% higher. In terms of the strength test of the parachute cord 23, the strength of the structural parachute cord 231 and the conductive parachute cord 232 is similar. The strength of the conductive parachute cord 232 is 2.63 MPa higher than that of the structural parachute cord 231. This may be due to the addition of copper wire 235 inside the structural parachute cord 231 compared to the conductive parachute cord 232. However, the tensile strength of the structural parachute cord 231 and the conductive parachute cord 232 is only about 62% of that of the control example. The main reason is that the parachute cord inner core 233 is a hollow structure, and the area of ​​the hollow part of the parachute cord inner core 233 is included when measuring the cross-sectional area of ​​the parachute cord, which will reduce the tensile strength. The secondary reason is that it is generally believed that the tensile strength of ultra-high molecular weight polyethylene is slightly lower than that of aramid, which also causes the tensile strength of the parachute cord to be lower than that of the control example.

[0117] (3) Power generation efficiency test

[0118] To evaluate the power generation efficiency of the textile solar energy device 21 under different lighting conditions, an LED array illumination box was used to simulate midday sunlight on Venus, Mars, Titan, and Earth's surface. The illumination intensities were set to 11,000 lx, 76,000 lx, 1,400 lx, and 114,000 lx, respectively. A digital illuminometer was used to calibrate the illumination intensity within the LED array illumination box, with an error within ±200 lx. The tested textile solar energy device 21 was a 10 cm x 10 cm square. A multimeter was used to measure the current and voltage across the busbars 41 at both ends of the textile solar energy device 21 under specific light intensities, and the generated power was calculated.

[0119] Table 4: Measurement results of power generation per unit area of ​​the embodiment and the control example under corresponding light intensity

[0120] Group Simulation Environment Light intensity (lx) Power generation (W) Example 1 Venus 11,000 4.2 Example 2 Mars 76,000 32 Example 3 Titan 1,400 0.6 Control Example Earth 114,000 48

[0121] Based on the power generation per square meter of the fabric solar energy supply device 21 of each embodiment under a specific light intensity measured through experiments in Table 4, combined with the total area of ​​the parachute canopy in each example, and the area ratio (i.e., the ratio of the fabric solar energy supply device 21 to the canopy base material), the total power generation of each embodiment is calculated.

[0122] Table 5 Comparison of total canopy area and total power generation under different embodiments

[0123] Group Total canopy area (m2) Area ratio Total power (kW) Example 1 20 1 0.8 Example 2 250 0.25 2.0 Example 3 63 1 0.4

[0124] Combining Tables 4 and 5, it can be seen that the textile solar energy device 21 can generate electricity normally under the lighting conditions of Examples 1-3. Example 3, which has the lowest power generation, can provide a total of 400W of electricity under the lighting conditions of Titan, which is greater than the 240W power of the RTG battery at the time of New Horizons launch and is sufficient to meet the power supply needs of the deep-hole probe. Example 2, which has the highest power generation, can provide 2000W of electricity under the lighting conditions of the Martian surface, exceeding the power generation of all currently operating Mars rovers.

[0125] (4) High temperature resistance test

[0126] The thermal stability of the fabric-based solar energy device 21 was evaluated using a thermogravimetric analyzer (TGA) to simulate the potential changes the material might experience on the surface of Venus, which has an average temperature of 462°C and is primarily composed of CO2. The material was first placed in a desiccator for 24 hours to minimize interference from volatile moisture in the fiber. The sample was then placed in an alumina crucible. The difference in mass between the crucible before and after sample loading was measured using a precision balance (accurate to 0.1 μg) as the initial sample mass, m0. The crucible was then placed firmly on the balance inside the TGA analyzer and heated from room temperature to 800°C at a rate of 10°C / min. The crucible was then protected in a nitrogen atmosphere (simulating the non-oxidizing atmosphere on the surface of Venus) and a nitrogen-oxygen mixture (simulating air, serving as a control) at a constant flow rate of 50 mL / min. Combined TG-DSC curves were recorded, and the thermal weight loss rates at 200°C, 500°C, and 800°C were analyzed.

[0127] The thermal weight loss (TG) was calculated using the following formula:

[0128] TG=(m0-m t ) / m0×100%

[0129] Where: m0 is the initial mass of the sample, m t For current quality

[0130] Table 6 Thermal weight loss rate of textile solar energy devices under different embodiments

[0131] Group Protective gas atmosphere TG (200℃) TG(500℃) TG (800℃) Example 1 100% nitrogen 2.69％ 9.73％ 25.45％ Control Example 80% nitrogen + 20% oxygen 3.29％ 14.46％ 92.42％

[0132] Table 6 shows that, whether Example 1 is heated in a pure nitrogen atmosphere or the control example is heated in a nitrogen-oxygen mixed atmosphere, the thermal weight loss of both is approximately 3% when heated to 200°C. This is due to the residual volatile components such as water and small molecular organic matter in the textile solar energy device 21. When heated to 500°C, the thermal weight loss rate of Example 1 reaches 9.73%, while the thermal weight loss rate of the control example is slightly higher than that of Example 1. Based on the thermal weight loss rate, it can be inferred that at this temperature, the aramid material in the textile solar energy device 21 undergoes a certain degree of thermal decomposition, but still has a certain structural strength. When heated to 800°C, the thermal weight loss rate of Example 1 reaches 25.45%, and the mass of the residual material reaches 74. The mass percentage of carbon in para-aramid is approximately 55%, which is close to the mass percentage of carbon in para-aramid of about 70% to 71%, indicating that most of the aramid in the textile solar energy supply device 21 has been carbonized. The color of the residue after thermogravimetric measurement has changed from golden yellow before heating to brown-black, and the volume has been significantly reduced. The warp 212 and the weft 211 have also spread out and cannot maintain the shape of the fabric. The thin-film solar cell 4 can be easily separated from the residue and its appearance has basically not changed. The thermal weight loss rate of the control example reaches 92.42%. After thermogravimetric measurement, the aramid part of the residue of the textile solar energy supply device 21 has basically turned into ashes, and the thin-film solar cell 4 has a white appearance, and its surface should have been oxidized and lost its power generation function.

[0133] The above four groups of experiments show that the use of the fabric solar energy supply device 21 to replace the canopy 22 base material in the present invention does not significantly increase the unit area weight of the parachute canopy fabric; the fabric solar energy supply device 21, the structural parachute rope and the conductive parachute rope all have good mechanical properties; under poor lighting conditions, the fabric solar energy supply device 21 can still generate electricity normally, and the total power generation under each embodiment is calculated based on the parachute area and light intensity in different embodiments; and under the working conditions simulated in specific embodiment 1, when the fabric solar energy supply device 21 is subjected to a temperature of 500°C for a short period of time, the fabric solar energy supply device 21 can generate electricity normally. The fabric-type solar energy supply device 21 can still maintain its structural integrity, eliminating the possibility of the parachute 2 fabric being damaged due to short-term high temperature during the lander's parachute descent. In a non-oxidizing atmosphere at a higher temperature, the organic material in the fabric-type solar energy supply device 21 is pyrolyzed in the high temperature environment of the Venus surface, and the thin-film solar cell 4 in the fabric-type solar energy supply device 21 is exposed. The thin-film solar cell 4 will not be damaged in the high temperature environment, thereby minimizing the obstruction of the thin-film solar cell due to overlapping or wrinkling of the parachute, thereby improving the power generation efficiency, which is consistent with the design requirements in Example 1.

[0134] In summary, the present invention, without significantly increasing the weight per unit area of ​​the parachute canopy fabric, replaces part of the warp threads 212 in the canopy 22 base material with thin-film solar cells 4, thereby preparing it into a flexible material with photovoltaic power generation function. The huge surface area of ​​the parachute carried by the deep space probe lander is used as an effective solar power generation area, thereby solving the problem of power generation shortage caused by insufficient sunlight on the surface of extraterrestrial bodies, providing sufficient electrical energy for the spacecraft, and proving that its power generation efficiency is higher than that of traditional solutions such as RTG and solar panels in any embodiment. Three auxiliary power supply devices are also designed, namely an airbag, a parachute rope tractor and a conductive parachute rope winder, which can connect the fabric solar energy supply device with the probe body, spread the parachute on the surface to increase the contact area between the fabric solar energy supply device on the parachute and sunlight, and prop up the parachute to prevent dust adhesion, thereby improving the service life and power generation efficiency of the power supply device in the present invention.

[0135] Although the present invention has been described in detail through the above preferred embodiments, it should be understood that the above description is not intended to limit the present invention. After reading the above description, various modifications and substitutions of the present invention will become apparent to those skilled in the art. Therefore, the scope of protection of the present invention should be defined by the appended claims.

Claims

1. A power supply device for deep space probes suitable for Venus, Mars, and Titan, characterized by: The invention comprises a detector body (1), a heat-insulating base (51), a heat-insulating cover (52), a parachute (2) and an auxiliary power supply device (3). The parachute (2) comprises an umbrella canopy (22) and an umbrella rope (23). Part or all of the umbrella canopy (22) is replaced by a fabric solar energy supply device (21). The total number of the umbrella ropes (23) should be a multiple of 12. The upper ends of the umbrella ropes are connected to the umbrella canopy (22). The lower sections are bundled into umbrella rope bundles (237) and fixed on the top of the heat-insulating cover (52), together forming the main structure of the parachute (2). The auxiliary power supply device (3) consists of three parts: a conductive umbrella rope winder (33), an umbrella rope tractor (32) and an air bag (31). The umbrella rope tractor ( The probe (32) is combined with the airbag (31) into a whole and is installed on the parachute rope (23). When the parachute (2) is in the open state, its position is limited to a certain distance above the parachute rope gathering point under the combined action of gravity and the elastic force of the parachute rope (23). The conductive parachute rope winder (33) is fixed inside the heat insulation cover (52) near the suspension point of the parachute rope bundle (237); when the probe is in the launch, cruise or re-entry state, the probe body (1) and the auxiliary power supply device (3) are protected inside the heat insulation bottom (51) and the heat insulation cover (52). A parachute compartment cover (53) is provided outside the heat insulation cover (52), and the parachute (2) is stored inside the parachute compartment cover (53).

2. The power supply device for deep space probes suitable for Venus, Mars, and Titan according to claim 1, characterized in that: The weaving method of the fabric-type solar energy supply device (21) includes an umbrella canopy (22) substrate, and the umbrella canopy (22) substrate is a plain weave fabric woven by interlacing warp threads (212) and weft threads (211) with one top and one bottom. On this basis, a part of the warp threads (212) in the umbrella canopy (22) substrate is replaced with a thin-film solar cell (4), and the thin-film solar cell (4) is the same width as the warp threads (212). The thin-film solar cell (4) alternately passes through three weft threads (211) and then passes under one weft thread (211) in the entire length of the substrate, and in sequence The loops are formed in a weaving pattern of three up and one down. After being separated from the thin-film solar cell (4) by three or more common warp threads (212), the warp threads (212) can be replaced by the thin-film solar cell (4) again. At this time, the weaving pattern of the thin-film solar cell (4) is the same as the above, but one weaving point is raised. The reinforcing thread (213) is woven into the fabric solar energy supply device (21) in a double plain weave or square plain weave at intervals in the weft direction. The reinforcing thread (213) is sewn at intervals of a multiple of 2 weft threads, and the sewing position is staggered with the thin-film solar cell (4).

3. The power supply device for deep space probes suitable for Venus, Mars, and Titan according to claim 1, characterized in that: The parachute rope (23) can be divided into two categories: a structural parachute rope (231) and a conductive parachute rope (232). The structural parachute rope (231) is made by coaxial braiding, and its interior is a parachute rope inner core (233) made of ultra-high molecular weight polyethylene, which is a hollow tubular structure. The outer side of the parachute rope inner core (233) is made of two layers of aramid fiber spirally braided in different directions to form a parachute rope outer core (234). The parachute rope inner core (233) is covered inside the parachute rope outer core (234); the conductive parachute rope (232) is based on the structural parachute rope (231), and a copper wire (235) is added to the hollow tubular interior of the parachute rope inner core (233). The copper wire (235) is bent at intervals to form a wire knot (236).

4. A power supply device for deep space probes suitable for Venus, Mars, and Titan according to claim 2 or 3, characterized in that: The fabric solar energy supply device (21) contains a plurality of thin-film solar cells (4), and bus bars (41) are respectively led out from both ends of the thin-film solar cells (4), wherein the bus bar (41) located at the upper part of the fabric solar energy supply device (21) starts from the top of the rightmost thin-film solar cell (4) in the fabric solar energy supply device (21), connects the tops of all the thin-film solar cells (4) in the fabric solar energy supply device (21) from right to left, and converges to the copper wire (235) in the conductive parachute rope (232) on the left; similarly, the bus bar (41) located at the lower part of the fabric solar energy supply device (21) starts from the bottom of the leftmost thin-film solar cell (4) in the fabric solar energy supply device (21), connects the bottoms of all the thin-film solar cells (4) in the fabric solar energy supply device (21) from left to right, and converges to the copper wire (235) in the conductive parachute rope (232) on the right.

5. The power supply device for deep space probes suitable for Venus, Mars and Titan according to claim 1 or 3, characterized in that: The structure of the parachute (2) is that the fabric solar energy supply device (21) and the canopy (22) are fixed on the structural parachute rope (231) and the conductive parachute rope (232) respectively; wherein the fabric solar energy supply device (21) and the canopy (22) can be fixed between two conductive parachute ropes (232), while only the canopy (22) is fixed between the conductive parachute ropes (232) and the structural parachute ropes (231).

6. The power supply device for deep space probes suitable for Venus, Mars, and Titan according to claim 1, characterized in that: The parachute rope tractor (32) includes a parachute rope tractor body (321), the parachute rope tractor body (321) is in the shape of a flat hexahedron, the top and bottom surfaces of which are square and the side surfaces are narrow and long rectangles, and the four side surfaces of the parachute rope tractor body (321) are respectively provided with rotating rods (322), the proximal end of the rotating rod (322) extends to the inside of the parachute rope tractor body (321) and is connected to the motor (324), and the rotating rod (322) is provided with a through hole (323) at the distal end position, and four parachute ropes (231) of the above structure are selected to pass through the through holes (323) respectively; the air bag (31) is installed on the parachute rope tractor in a folded state On the top surface of the main body (321), a small hole is opened on the wall of the air bag (31) and an air guide tube (313) is led out. The other end of the air guide tube (313) extends to the micro fan (312) after penetrating the one-way valve (311) and is fixedly connected to the air outlet thereon; the conductive parachute cord winder (33) includes a conductive parachute cord storage cylinder (331), the conductive parachute cord storage cylinder (331) is fixed to the top of the inner side of the heat insulation cover (52) and a conductive parachute cord storage cylinder core (332) is provided inside the conductive parachute cord storage cylinder (331), one end of the conductive parachute cord storage cylinder (331) is closed and the other end is open, and a combing ring ( 333), an outer guide wheel (334) and an inner guide wheel (335), and the combing ring (333), the outer guide wheel (334) and the inner guide wheel (335) are all fixed on the inner inclined wall surface of the heat insulation cover (52), the conductive parachute rope (232) is wound layer by layer on the conductive parachute rope storage tube core (332) and is stored in the conductive parachute rope storage tube (331), one end of which extends from the closed end of the conductive parachute rope storage tube (331) and passes through the heat insulation cover (52) to the parachute rope bundle (237) hanging point, and is connected to the conductive parachute rope (232) on the parachute (2) through the parachute rope bundle (237), and the other end is extended from the opening of the conductive parachute rope storage tube (331) After passing through the combing ring (333), the outer guide wheel (334) and the inner guide wheel (335), it is connected to the detector body (1); further, the outer guide wheel (334) and the inner guide wheel (335) are provided with grooves, the conductive parachute rope (232) is tangent to the side of the outer guide wheel (334) away from the heat shield (52) and is embedded in the groove on the outer guide wheel (334), and similarly, the conductive parachute rope (232) is tangent to the side of the inner guide wheel (335) close to the heat shield (52) and is embedded in the groove on the inner guide wheel (335), and a tension adjustment spring (336) is provided at the connection between the outer guide wheel (334) and the heat shield (52).

7. The power supply device for deep space probes suitable for Venus, Mars, and Titan according to claim 2, characterized in that: The material of the thin film solar cell (4) is selected from one or more mixtures of copper indium gallium selenide solar cells, perovskite solar cells, and polymer solar cells.

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