CN114655444A - Parachute system for planet detection - Google Patents
Parachute system for planet detection Download PDFInfo
- Publication number
- CN114655444A CN114655444A CN202210308262.9A CN202210308262A CN114655444A CN 114655444 A CN114655444 A CN 114655444A CN 202210308262 A CN202210308262 A CN 202210308262A CN 114655444 A CN114655444 A CN 114655444A
- Authority
- CN
- China
- Prior art keywords
- parachute
- sensor
- umbrella
- repair
- planetary
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000001514 detection method Methods 0.000 title claims abstract description 20
- 230000008439 repair process Effects 0.000 claims abstract description 56
- 239000000428 dust Substances 0.000 claims abstract description 38
- 239000004744 fabric Substances 0.000 claims description 59
- 239000000463 material Substances 0.000 claims description 8
- 230000009471 action Effects 0.000 claims description 7
- 229920001169 thermoplastic Polymers 0.000 claims description 4
- 239000004416 thermosoftening plastic Substances 0.000 claims description 4
- 239000002131 composite material Substances 0.000 claims description 3
- 239000002245 particle Substances 0.000 abstract description 19
- 230000006872 improvement Effects 0.000 description 8
- 239000000835 fiber Substances 0.000 description 6
- 238000000034 method Methods 0.000 description 6
- 230000008569 process Effects 0.000 description 6
- 239000004760 aramid Substances 0.000 description 5
- 229920003235 aromatic polyamide Polymers 0.000 description 5
- 229920000728 polyester Polymers 0.000 description 5
- 239000004753 textile Substances 0.000 description 4
- 230000001681 protective effect Effects 0.000 description 3
- 229920006231 aramid fiber Polymers 0.000 description 2
- 238000012937 correction Methods 0.000 description 2
- 230000000875 corresponding effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000005284 excitation Effects 0.000 description 2
- 230000001771 impaired effect Effects 0.000 description 2
- 239000007769 metal material Substances 0.000 description 2
- 239000004576 sand Substances 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 240000000491 Corchorus aestuans Species 0.000 description 1
- 235000011777 Corchorus aestuans Nutrition 0.000 description 1
- 235000010862 Corchorus capsularis Nutrition 0.000 description 1
- 239000000443 aerosol Substances 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000002596 correlated effect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000004069 differentiation Effects 0.000 description 1
- 239000006185 dispersion Substances 0.000 description 1
- 239000003733 fiber-reinforced composite Substances 0.000 description 1
- 239000011888 foil Substances 0.000 description 1
- 239000011810 insulating material Substances 0.000 description 1
- WABPQHHGFIMREM-UHFFFAOYSA-N lead(0) Chemical compound [Pb] WABPQHHGFIMREM-UHFFFAOYSA-N 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 229910052755 nonmetal Inorganic materials 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000011056 performance test Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 239000002689 soil Substances 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D17/00—Parachutes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D17/00—Parachutes
- B64D17/02—Canopy arrangement or construction
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Geophysics And Detection Of Objects (AREA)
Abstract
The embodiment of the invention discloses a parachute system for planetary detection. According to the parachute system for planet detection provided by the embodiment of the invention, the sensor and the repair structure are arranged on the parachute main body, and the impact strength of dust particles is monitored through the sensor, so that the impact damage of the dust particles to the parachute main body is accurately evaluated; the repair structure repairs damage of the parachute due to dust impact based on sensor signals of the sensor, and closed-loop control and real-time automatic repair are achieved.
Description
Technical Field
The invention relates to the technical field of near-earth detection, in particular to a parachute system for planetary detection.
Background
In recent years, close-proximity probing has become a popular probing task. Because the planet atmospheric environment has the characteristics of dryness and large day and night temperature difference, extreme weather such as sand storm and the like often exists near the ground surface. Under the action of strong wind, the dry and loose planet surface soil particles can rise to several kilometers or even dozens of kilometers, and dense dust aerosol is formed on the planet surface. In the process of planet detection near the ground, dust particles moving at high speed randomly impact the surface of a detector parachute to damage the structure of the parachute body, and serious threat is caused to the safety of the parachute.
Therefore, in view of the above technical problems, there is a need for a parachute system for planetary detection capable of monitoring the impact strength of dust particles and self-repairing damage due to dust impact.
Disclosure of Invention
In view of the above, in order to solve the above problems, an object of an embodiment of the present invention is to provide a parachute system for planetary exploration.
In order to achieve the above purpose, the technical solutions provided by the embodiments of the present invention are as follows: a parachute system for planetary exploration comprising: the parachute comprises a parachute main body, a landing part and a connecting part, wherein the connecting part is used for connecting the parachute main body and the landing part; the sensor is arranged on the umbrella main body and used for detecting the impact force of dust and generating a sensing signal; and the repairing structure is arranged on the umbrella main body and is electrically connected with the sensor, and the repairing structure carries out repairing action based on the sensing signal.
As a further improvement of the present invention, the umbrella main body comprises umbrella ribs and an umbrella cover, and the umbrella ribs divide the umbrella cover into at least four umbrella areas.
As a further development of the invention, at least three sensors and at least two repair structures are arranged in each umbrella area.
As a further improvement of the present invention, at least one of the at least three sensors is disposed in a top region of the umbrella area, and at least two of the at least three sensors are circumferentially disposed in a bottom region of the umbrella area.
As a further improvement of the present invention, at least one of the at least two repair structures is disposed at a top area of the umbrella area and is electrically connected to a sensor disposed at the top area of the umbrella area; at least one restoration structure in the at least two restoration structures is arranged in the bottom area of the umbrella area and is electrically connected with a sensor circumferentially arranged in the bottom area of the umbrella area.
As a further improvement of the invention, the umbrella cover is made of flexible materials, and the umbrella ribs are made of thermoplastic composite materials.
As a further improvement of the invention, the sensor comprises a first electrode plate, a first fabric layer, an insulating layer, a second fabric layer and a second electrode plate which are sequentially arranged.
As a further improvement of the invention, the electrical polarity of the first textile layer is opposite to the electrical polarity of the second textile layer.
As a further improvement of the present invention, the repair structure includes a connecting member, a repair rod member, a folding member, and a fuse, the fuse is configured to receive the sensing signal and to fuse when the sensing signal is greater than a preset threshold, and the folding member automatically unfolds a folding portion of the folding member after the fuse fuses.
As a further improvement of the present invention, the fuse includes a spring, a connection electrode electrically connected to the sensor, and a fuse electrically connected to the connection electrode.
The invention has the following advantages:
according to the parachute system for planet detection provided by the embodiment of the invention, the sensor and the repair structure are arranged on the parachute main body, and the impact strength of dust particles is monitored through the sensor, so that the impact damage of the dust particles to the parachute main body is accurately evaluated; the repairing structure repairs damage of the parachute due to dust impact based on sensor signals of the sensor, and closed-loop control and real-time self repair are achieved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments described in the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is a perspective view illustrating a parachute system for planetary exploration according to an embodiment of the present invention;
FIG. 2 is a schematic plan view from another perspective of the embodiment shown in FIG. 1;
fig. 3 is a schematic perspective view of a sensor according to an embodiment of the present invention;
fig. 4 is a schematic perspective view of a repair structure according to an embodiment of the present invention;
FIG. 5 is a schematic perspective view of a connector of the prosthetic structure of the embodiment of FIG. 4;
FIG. 6 is a schematic perspective view of a repair rod of the repair structure of the embodiment shown in FIG. 4;
fig. 7 is a schematic perspective view of a fuse of the repair structure of the embodiment shown in fig. 4.
Notations in the figures:
100. parachute system 10 for planetary exploration, parachute main body 20, and connection part
30. Landing part 40(40 '), sensor 50 (50'), repair structure 110, and umbrella rib
101(102, 103\104\105\106\107\108), an umbrella area 43 and a first electrode plate
46. A second electrode plate 42, an insulating layer 44, a first fabric layer 45, a second fabric layer
51. Connecting piece 53, folding piece 52, repair rod piece 54 and fuse
511. Nail shaft 512, insulating layer 521, through hole 523 and through part
541. Protective sleeve 542, spring 544, fuse 543 and electrode
41(513), lead wire
Detailed Description
In order to make those skilled in the art better understand the technical solution of the present invention, the technical solution in the embodiment of the present invention will be clearly and completely described below with reference to the drawings in the embodiment of the present invention, and it is obvious that the described embodiment is only a part of the embodiment of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
As shown in fig. 1, an embodiment of the present invention provides a perspective structure diagram of a parachute system for planetary exploration. In this embodiment, the parachute system 100 for planetary detection comprises a parachute, a sensor 40 and a repair structure 50. The parachute comprises a parachute body 10, a landing part 30, and a connecting part 20 for connecting the parachute body 10 and the landing part 30. In a particular embodiment, the landing section 30 is a ground proximity detector and the connecting section 20 is a connecting string. Wherein, sensor 40 is arranged on umbrella main body 10 for detecting the impact force of dust and generating a sensing signal. The restoration structure 50 is provided on the umbrella main body 10 and electrically connected to the sensor 40, and the restoration structure 50 performs a restoration operation based on a sensing signal generated by the sensor 40.
The umbrella main body 10 includes ribs and a canopy. From the structural symmetry point of view, the umbrella surface is divided into at least four umbrella areas by the umbrella ribs. With continued reference to fig. 2, in this embodiment, a plurality of ribs 110 divide the canopy into 8 umbrella areas, umbrella area 101, umbrella area 102, umbrella area 103, umbrella area 104, umbrella area 105, umbrella area 106, umbrella area 107, umbrella area 108. Preferably, the shape and area of each umbrella area are uniform. The umbrella cover is made of flexible materials, such as flexible aramid fabrics. The ribs 110 are made of a thermoplastic composite material. The material of the main body 10 is set to ensure the overall flexibility of the parachute system, effectively improving the reliability of the entire system.
At least three sensors and at least two repair structures are arranged in each umbrella area. Wherein at least one sensor of the at least three sensors is arranged in the top area of the umbrella area, which can also be called a radial sensor; at least two of the at least three sensors are circumferentially arranged in a bottom area of the umbrella area, and may also be referred to as circumferential sensors. Wherein at least one of the at least two repair structures is disposed at a top region of the umbrella area and is electrically connected to a sensor disposed at the top region of the umbrella area, where the repair structure may also be referred to as a radial repair structure; at least one of the at least two repair structures is arranged in the bottom area of the umbrella area and is electrically connected with the sensor circumferentially arranged in the bottom area of the umbrella area, and the repair structure can also be called a circumferential repair structure. Through set up radial sensor and restoration structure and circumference sensor and restoration structure respectively in same umbrella district, promoted the prosthetic reliability of parachute and improved the parachute reply dust striking impaired back selfreparing robustness. Preferably, the sensor is pasted inside the umbrella face through insulating tape, and the repair structure is also arranged inside the umbrella face, so that the impact of dust on the straight planet of the sensor and the repair structure is effectively avoided, and the damage rate of the sensor and the repair structure caused by the severe planet environment is reduced.
In order to more clearly explain the technical solution, whether the technical solution is arranged in the radial direction or in the circumferential direction is distinguished, a single reference number is used above the corresponding reference number in the process of the description herein to indicate the distinction. With continued reference to fig. 2, in this embodiment, each umbrella area is provided with one radial repair structure 50 'and one radial sensor 40', three circumferential sensors 40 and two circumferential repair structures 50. The radial repair structure 50 'is electrically connected to the radial sensor 40', and the radial repair structure 50 'performs a repair action based on the sensing signal generated by the radial sensor 40'. Two circumferential repair structures 50 are respectively arranged at intervals between three circumferential sensors 40, and each circumferential repair structure 50 is electrically connected with two adjacent circumferential sensors 40 respectively. Each circumferential repair structure 50 performs a repair action based on the sensing signals generated by two adjacent circumferential sensors 40.
In this embodiment, the parachute system 100 for planetary exploration has a simple structural design, flexibility in the overall structure, and high reliability.
As shown in fig. 3, a schematic diagram of a sensor structure according to an embodiment of the present invention is provided. In this embodiment, the sensor 40 includes a first electrode plate 43, a first fabric layer 44, an insulating layer 42, a second fabric layer 45, and a second electrode plate 46, which are arranged in this order. Wherein, the first electrode plate 43 or the second electrode plate 46 is used for receiving the impact of dust, and the electric polarities of the first fabric layer 44 and the second fabric layer 45 are opposite. Further, the sensor 40 further includes a wire 41, and the wire 41 passes through the insulating layer 42. The wire 41 conducts an electric signal generated by the sensor 40 after dust strikes the first electrode plate 43 or the second electrode plate 46.
In this embodiment, the sensor 40 is a friction sensor, and when the conventional friction sensor is used for precisely detecting a scene, various detection circuits and control systems need to be matched. In this embodiment, the structural arrangement of the sensor 40 enables the parachute system to only use the friction electric sensor alone to realize the accurate detection of dust particles, and other circuits and power supply input are not needed, so that the parachute system is simple in structure and high in reliability.
The first electrode plate 43 and the second electrode plate 46 are made of metal material, such as aluminum foil electrodes, and are respectively used as a positive electrode plate and a negative electrode plate of the sensor 40. The first fabric layer 44 and the second fabric layer 45 are made of tough non-metal materials, and the first fabric layer 44 and the second fabric layer 45 have opposite electrical polarities, higher output voltage and certain flexibility. In a particular embodiment, the first fabric layer 44 is an aramid fabric and the second fabric layer 45 is a polyester fabric; alternatively, the first fabric layer 44 is a carbon fiber fabric layer and the second fabric layer 45 is a jute fiber fabric layer. Preferably, the inner surface of first textile layer 44 and/or the inner surface of second textile layer 45 are metallized to further enhance electrode differentiation.
For the sake of simple processing and simple arrangement, it is preferable that the size of the first electrode plate 43, the size of the first fabric layer 44, the size of the second fabric layer 45, and the size of the second electrode plate 46 are kept the same. Wherein, the insulating layer 42 has a size larger than the first electrode plate 43, the first fabric layer 44, the second fabric layer 45 or the second electrode plate 46, respectively.
Further, the sensor 40 also includes an insulating sealing layer (not shown in the drawings) to better protect the sensor 40 and facilitate the adhesion of the sensor 40 to the parachute body. The insulating sealing layer seals the first electrode plate 43, the first fabric layer 44, the insulating layer 42, the second fabric layer 45 and the second electrode plate 46 into a whole.
When dust impacts the sensor 40 to generate impact force, the first electrode plate 43 and the second electrode plate 46 of the sensor 40 are separated, opposite charges between the surface of the first fabric layer 44 and the surface of the second fabric layer 45 are separated, and a potential difference is generated between the first electrode plate 43 and the second electrode plate 46; after the impact force is generated by the dust striking the sensor 40, the first electrode plate 43 and the second electrode plate 46 are gradually closed from the separated state, so that the sensor 40 generates a pulse signal, which is a sensing signal.
The calculation of the impact force according to classical mechanics is disclosed as follows:
in the formula 1, F is the impact force of dust particles, m is the mass of the dust particles, v is the mass impact speed of the dust particles, and delta t is the impact time.
In the embodiment of the invention, the damage judgment model of the parachute umbrella fabric is set as follows:
wherein d is the damage value of the parachute canopy, epsilon12、ε13、ε23Respectively the shear force, T, to which the fabric is subjected in three orthogonal planes12、T13、T23The corresponding shear strength is shown below.
Wherein S is the cross-sectional area of the single bundle of fibers of the fiber fabric, l1、l2The length and the width of the fiber fabric parallelogram unit cell are respectively, and D is the diameter of the fiber fabric single bundle fiber of the umbrella cover of the parachute. Thus is provided with
According to the study statistics, the dust particle size and shape are positively correlated to the impact force. On the premise of certain mass, the larger the dust particle size is, the more serious the impact damage is; the larger the dispersion degree of each section size of the particles is, the more serious the impact damage is; for this reason, the parachute damage determination is corrected as follows:
wherein x is a dust particle size correction parameter and y is a dust particle shape correction parameter.
According to the traditional mechanics, the impact energy E is calculated as follows
According to the data of the sand storm on the surfaces of different planets, the energy limit borne by the parachute umbrella cover can be evaluated.
Unifying energy and damage factor to obtain
In this particular embodiment, due to the difference in electronegativity of the aramid of the first fabric layer 44 and the polyester of the second fabric layer 45, the negative charge of the surface of the aramid fabric and the positive charge of the surface of the polyester fabric are initially present. Since the positive and negative charges are in close contact, the entire sensor does not exhibit any electrical output in this initial state. When the parachute umbrella surface is impacted by dust particles near the surface of the ground, the positive electrode plate and the negative electrode plate of the sensor are separated, and meanwhile, opposite charges on the surface of the aramid fiber fabric and the surface of the polyester fabric are also separated, so that potential difference exists between the positive electrode and the negative electrode of the sensor. When the dust particles impact the surface of the parachute, the impact energy is released, the positive electrode plate and the negative electrode plate are gradually closed, the sensor recovers to the original state, and the sensor generates a pulse voltage signal in the process. Each pulse signal reflects a collision process between dust and parachute fabric, and the dust impact on the parachute can be estimated by detecting the peak value and the number of the pulse signals.
The relationship between the sensor pulse signal voltage and the dust impact energy is as follows:
V＝k*E (10)
wherein V is the peak value of the sensor pulse signal, E is the dust impact energy, and k is the distance coefficient, and is related to the surface atmospheric density according to the experimental determination.
Further, in the above-mentioned case,
thereby obtaining the relationship between the damage condition and the pulse signal of the friction point sensor.
According to the statistics of relevant data of different planet near-ground surface sandstorms and the strength of the fabric material of the parachute fabric, the value range of the damage factor d of the parachute fabric in the planet near-ground detection process can be calculated through the combination formula (7), so that the critical damage electrical signal threshold of the parachute fabric is determined, and electrical signal input is provided for the electric excitation self-repairing folding structure.
In this embodiment, sensor 40 can monitor accurately that the parachute umbrella face receives the dust impact, and a plurality of sensors 40 are arranged respectively to a plurality of umbrella areas and the position of impaired umbrella face can be monitored accurately, provide accurate restoration signal for parachute system's restoration structure. Further, the sensor 40 can generate a sensing signal when being impacted by dust, and the application environment scene of planet detection is facilitated without the assistance of a circuit or a control system.
As shown in fig. 4, a schematic perspective structure of a repair structure according to an embodiment of the present invention is provided. The repair structure 50 includes a connecting member 51, a repair bar 52, a folding member 53, and a fuse 54. The connector 51 is used to secure the prosthetic structure 50 to the umbrella body 10 of the parachute. The folder 53 is used for repairing a damaged portion of the parachute; the folding member 53 has a folded state and an unfolded state, and the initial state of the folding member 53 is the folded state. The two ends of the repair rod 52 are respectively fixed with the connecting piece 51, and a folding piece 53 is arranged between the two repair rod 53. The fuse 54 is disposed in the folding member 53, the fuse 54 is configured to receive a sensing signal generated by the sensor 40 and to be fused when the sensing signal is greater than a preset threshold, and the folding member 53 is transformed from the folded state to the unfolded state after the fuse 54 is fused.
As shown in fig. 5, in this embodiment, the connector 51 includes a nail shaft 511, an insulating sheath 512, and a wire 513. The nail shaft 511 is used to be fixed to the umbrella body 10 of the parachute. The insulating sleeve 512 is sleeved on the nail shaft 511, and the insulating sleeve 512 is provided with a groove (not shown in the figure). The insulating sheath 512 is made of rubber material and has a groove in the middle thereof for accommodating the conductive wire 513. A wire 513 is disposed in the recess, one end of the wire 513 being connected to the sensor 40 that generates the sensing signal, and the other end of the wire 513 being connected to the fuse 54.
As shown in fig. 6, in this embodiment, through holes 521 are respectively formed at both ends of the rod of the repair rod 52, and the connecting member 51 is inserted into the through holes 521. Specifically, the diameter of the nail shaft 511 is the same as the diameter of the through hole 521, and the nail shaft 511 and the through hole 521 are fitted to each other. The length of the nail shaft 511 is greater than the shaft thickness of the restoration lever 52, and preferably, the length of the nail shaft 511 is three times the shaft thickness of the restoration lever 52. The shaft portion of the repair rod 52 is penetrated, and the penetrated portion may be defined as a penetrating portion 523. Wherein the through portion 523 is used to store the folder 53. The repair rod 52 is flexible and can be made of thermoplastic-based aramid fiber reinforced composite material, so that the overall flexibility of the parachute is not affected.
The initial state of the folding member 53 is a folded state, forming a folded portion. After the fuse 54 is fused, the folding member 53 automatically unfolds the folded portion to repair the damaged portion of the parachute main body. Preferably, the folding members 53 are of a material that conforms to the canopy of the parachute, thereby enabling the repaired parachute to have a uniform shape.
As shown in fig. 7, the fuse 54 includes a protective sheath 541, a spring 542, a fuse 544, and an electrode 543. The protection cover 541 is made of an insulating material and has a hollow channel. A spring 542 is disposed in the hollow passage; the spring 542 has a compressed state and a natural state, and the initial state of the spring 542 is the compressed state. The curvature of the spring 542 is consistent with that of the parachute main body of the parachute, and flexible unfolding of the repair structure in the repair process can be achieved to be better consistent with that of the parachute main body of the parachute. A fuse 544 is disposed through the hollow passage of the spring 542. The electrode 543 is disposed at the end of the fuse 544 and electrically connected to the fuse 544. Preferably, the fuse is a fuse of the fuse type. The curvature of the fuse is consistent with that of the parachute main body of the parachute, and the repairing structure can be flexibly unfolded in the repairing process to be better consistent with that of the parachute main body of the parachute. When the parachute main body is not subjected to impact of dust, the spring 542 is in a compressed state, and the spring 542 is restrained by the protective cover 541 and the fuse 544.
In this embodiment, the repair structure 50 performs a repair action based on electrical excitation, which may achieve closed-loop real-time self-repair. Further, the repair structure 50 may set a rated signal of the fuse according to a specific planetary detection task and an umbrella cover condition of the parachute, obtain a related preset threshold, and adaptively perform a change of different tasks and scenes.
According to the above equation (1), when the sensor 40 is struck by dust particles, a pulse voltage is generated. According to the performance test of the parachute, the impact energy threshold value which can be borne by the parachute umbrella cover structure in the near-ground space detection can be obtained, and then the pulse voltage threshold value of the sensor 40 is obtained through calculation. The rated voltage or rated current of the fuse used for detecting the parachute at different near-ground surfaces is determined according to the pulse voltage threshold.
When the parachute is impacted by dust to cause the umbrella surface structure to be damaged, the sensor 40 generates pulse voltage exceeding a preset threshold value, current is transmitted to the fuse 54 through the conducting wires 41(513), the fuse 544 in the fuse 54 is fused, the spring 542 is out of restraint, and transverse tension is generated. Under the action of the spring 542, the repairing rod 52 rotates around the connecting piece 51, the folding part of the folding piece 53 is unfolded, and the umbrella cover between the connecting rods is also unfolded. The repair rods 52 ensure the overall structural strength of the damaged parachute body, and the folding pieces 53 between the repair rods 52 can fill up the damaged holes of the parachute cover, so that the self-repair of the parachute is realized.
It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.
Claims (10)
1. A parachute system for planetary exploration, comprising:
the parachute comprises a parachute main body, a landing part and a connecting part, wherein the connecting part is used for connecting the parachute main body and the landing part;
the sensor is arranged on the umbrella main body and used for detecting the impact force of dust and generating a sensing signal;
and the repairing structure is arranged on the umbrella main body and is electrically connected with the sensor, and the repairing structure carries out repairing action based on the sensing signal.
2. A parachute system for planetary exploration according to claim 1, wherein said parachute body comprises umbrella ribs and a canopy, said umbrella ribs dividing said canopy into at least four canopy zones.
3. A parachute system for planetary detection as in claim 2 wherein at least three sensors and at least two repair structures are provided within each parachute bay.
4. A parachute system for planetary detection as in claim 3 wherein at least one of the at least three sensors is disposed at a top region of the parachute bay and at least two of the at least three sensors are circumferentially disposed at a bottom region of the parachute bay.
5. A parachute system for planetary detection according to claim 4, wherein at least one of the at least two restoring structures is disposed at a top area of the parachute bay and is electrically connected to a sensor disposed at the top area of the parachute bay; at least one restoration structure in the at least two restoration structures is arranged in the bottom area of the umbrella area and is electrically connected with a sensor circumferentially arranged in the bottom area of the umbrella area.
6. A parachute system for planetary exploration according to claim 1, wherein said canopy is made of a flexible material and said ribs are made of a thermoplastic composite material.
7. A parachute system for planetary exploration according to claim 1, wherein said sensor comprises a first electrode plate, a first fabric layer, an insulating layer, a second fabric layer and a second electrode plate arranged in sequence.
8. A parachute system for planetary exploration according to claim 7, wherein said first fabric layer and said second fabric layer have opposite electrical polarities.
9. A parachute system for planetary detection according to claim 1, wherein the repair structure comprises a connecting member, a repair rod member, a folding member, and a fuse for receiving the sensing signal and fusing when the sensing signal is greater than a preset threshold, the folding member automatically unfolding a folded portion of the folding member after the fuse is fused.
10. A parachute system for planetary exploration according to claim 9, wherein said fuse comprises a spring, a connection electrode electrically connected with a sensor, and a fuse electrically connected with said connection electrode.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210308262.9A CN114655444A (en) | 2022-03-26 | 2022-03-26 | Parachute system for planet detection |
| PCT/CN2022/126988 WO2023184945A1 (en) | 2022-03-26 | 2022-10-24 | Parachute system for planetary exploration |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210308262.9A CN114655444A (en) | 2022-03-26 | 2022-03-26 | Parachute system for planet detection |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114655444A true CN114655444A (en) | 2022-06-24 |
Family
ID=82033142
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210308262.9A Pending CN114655444A (en) | 2022-03-26 | 2022-03-26 | Parachute system for planet detection |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN114655444A (en) |
| WO (1) | WO2023184945A1 (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11738885B1 (en) | 2022-03-26 | 2023-08-29 | Soochow University | Monitoring and repair method for planetary exploration parachute system |
| WO2023184945A1 (en) * | 2022-03-26 | 2023-10-05 | 苏州大学 | Parachute system for planetary exploration |
| WO2023184946A1 (en) * | 2022-03-26 | 2023-10-05 | 苏州大学 | Repair system for repairing planet detection parachute |
| WO2023184947A1 (en) * | 2022-03-26 | 2023-10-05 | 苏州大学 | Monitoring and repairing method for parachute system for planetary exploration |
Family Cites Families (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19906970C2 (en) * | 1999-02-19 | 2003-03-27 | Rheinmetall W & M Gmbh | reconnaissance probe |
| CN105127975B (en) * | 2015-09-24 | 2017-04-19 | 北京空间飞行器总体设计部 | Walking robot having landing buffer function |
| US11130585B2 (en) * | 2017-08-30 | 2021-09-28 | Nippon Kayaku Kabushiki Kaisha | Aerial vehicle |
| CN108298093A (en) * | 2018-01-26 | 2018-07-20 | 大连理工大学 | Parachute rope draw off gear |
| JP7013319B2 (en) * | 2018-05-11 | 2022-01-31 | 日本化薬株式会社 | Shock shock absorbers and flying objects equipped with shock shock absorbers |
| CN111516883B (en) * | 2020-05-01 | 2021-08-31 | 泉州市桥东商贸有限公司 | Parachute structure with combined skeleton and high-altitude restoration of crevasses |
| CN114671030A (en) * | 2022-03-26 | 2022-06-28 | 苏州大学 | A repair system for repairing parachute that planet was surveyed |
| CN114655444A (en) * | 2022-03-26 | 2022-06-24 | 苏州大学 | Parachute system for planet detection |
| CN217304227U (en) * | 2022-03-26 | 2022-08-26 | 苏州大学 | Sensor for detecting dust impact |
| CN114777975B (en) * | 2022-03-26 | 2023-10-24 | 苏州大学 | Monitoring and repairing method of parachute system for planetary detection |
-
2022
- 2022-03-26 CN CN202210308262.9A patent/CN114655444A/en active Pending
- 2022-10-24 WO PCT/CN2022/126988 patent/WO2023184945A1/en unknown
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11738885B1 (en) | 2022-03-26 | 2023-08-29 | Soochow University | Monitoring and repair method for planetary exploration parachute system |
| WO2023184945A1 (en) * | 2022-03-26 | 2023-10-05 | 苏州大学 | Parachute system for planetary exploration |
| WO2023184946A1 (en) * | 2022-03-26 | 2023-10-05 | 苏州大学 | Repair system for repairing planet detection parachute |
| WO2023184947A1 (en) * | 2022-03-26 | 2023-10-05 | 苏州大学 | Monitoring and repairing method for parachute system for planetary exploration |
| US11905021B2 (en) | 2022-03-26 | 2024-02-20 | Soochow University | Repair system for planetary exploration parachute |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2023184945A1 (en) | 2023-10-05 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN114655444A (en) | Parachute system for planet detection | |
| CN114777975B (en) | Monitoring and repairing method of parachute system for planetary detection | |
| CN217304227U (en) | Sensor for detecting dust impact | |
| CN114671030A (en) | A repair system for repairing parachute that planet was surveyed | |
| Katz et al. | Mechanism for spacecraft charging initiated destruction of solar arrays in GEO | |
| US7377750B1 (en) | Lightning protection system for a wind turbine | |
| JP6305450B2 (en) | Wind power generator blade and wind power generator blade inspection method | |
| CN201763543U (en) | System for protecting wind turbine from being struck by lightning and wind turbine | |
| EP0938141A2 (en) | Solar array | |
| CN103615938B (en) | Missile folded wing developing test device | |
| KR102079446B1 (en) | Electric energy charging system and Electric energy charging method | |
| CA2768493A1 (en) | System for protecting wind turbines against atmospheric discharges | |
| US11738885B1 (en) | Monitoring and repair method for planetary exploration parachute system | |
| US8593165B2 (en) | Solar generator | |
| US20160261210A1 (en) | Triboelectric energy harvester using electrolyte | |
| EncinasPlaza et al. | Xatcobeo: Small Mechanisms for CubeSat Satellites-Antenna and Solar Array Deployment | |
| KR102080411B1 (en) | Fabric type smart grid sensor | |
| CN111806671A (en) | Panel for an aircraft cabin | |
| Ferguson et al. | First results from the floating potential probe (FPP) on the international space station | |
| JP2018053900A (en) | Blade for wind power generator and method for inspecting blade for wind power generator | |
| Gopalan et al. | A new technique for visualization of shock shapes in hypersonic shock tunnel | |
| US7032457B1 (en) | Method and apparatus for dielectric sensors and smart skin for aircraft and space vehicles | |
| Rodrigues et al. | Plasma actuators optimization using stair shaped dielectric layers | |
| Sizhan et al. | Study On Electrostatic Discharge Test Method of High-voltage Solar Cell Array | |
| JP2003252300A (en) | Retention release mechanism |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |