CN113022839A - Combined type large-load high-altitude floating test platform and flying method thereof - Google Patents
Combined type large-load high-altitude floating test platform and flying method thereof Download PDFInfo
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- CN113022839A CN113022839A CN202110441982.8A CN202110441982A CN113022839A CN 113022839 A CN113022839 A CN 113022839A CN 202110441982 A CN202110441982 A CN 202110441982A CN 113022839 A CN113022839 A CN 113022839A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/40—Balloons
- B64B1/50—Captive balloons
- B64B1/52—Captive balloons attaching trailing entanglements
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/40—Balloons
- B64B1/50—Captive balloons
- B64B1/54—Captive balloons connecting two or more balloons in superimposed relationship
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Abstract
The invention discloses a combined large-load high-altitude floating test platform and a flying method thereof, wherein the test platform comprises a main zero-pressure ball, a plurality of auxiliary zero-pressure balls, a main cable, a plurality of auxiliary cables and a load cabin; the ball handle is connected with a main cable after the main zero-pressure ball is inflated, and the load cabin is connected with the lower end of the main cable; one end of each of the auxiliary cables is connected to the main cable at a designed interval; after each auxiliary zero-pressure ball is inflated, the ball handle of each auxiliary zero-pressure ball is connected with the other end of one auxiliary cable; after the test platform is lifted off, the main zero-pressure balloon is positioned at the uppermost end, and the main zero-pressure balloon is not in contact with the auxiliary zero-pressure balloon and the auxiliary zero-pressure balloon. The manufacturing cost of the zero-pressure ball is low, and the test cost is greatly reduced. The ground windproof fixing device is simple in structure and configuration, convenient to operate, low in requirement on test sites, and few in required staff when the test platform is flown. And releasing the load after the test platform reaches the task altitude, and rapidly ascending the zero-pressure balloon to the maximum altitude for blasting without the problem of subsequent flight airspace.
Description
Technical Field
The invention belongs to the technical field of high-altitude aerostats, and particularly relates to a combined large-load high-altitude aerostats test platform and a flying method thereof.
Background
In the field of aerostat, if a heavy target load (100 kg and above) is transported to an adjacent space with an altitude of 20Km and above and is temporarily parked in the air, three technical approaches of stratospheric airship, captive balloon and free balloon are available at present, wherein the captive balloon is difficult to achieve due to the higher the lift-off height, the longer the captive cable, resulting in less weight of the transportable payload, for stratospheric airships, six stratospheric unmanned airships including a "climber" high altitude airship, a japanese stratospheric airship, a Hi Sentinel 20, a Hi Sentinel 50, a Hi Sentinel 80 and a "skyscraper" airship have been verified to have entered the stratospheric altitude, but carry a payload far below 100 kg, it is only possible to achieve the above task with a super-pressurized balloon and a zero-pressurized balloon in a free balloon.
Regarding the high-altitude aerostat with large load, the flying test conditions of ultra-long overpressure balloons in recent years of NASA in USA are the flying tests with the flying numbers of 591NT, 608NT, 616NT, 631NT, 659NT, 662NT and 669, the effective load of the ultra-long overpressure balloons reaches more than 300 kilograms, the flying height reaches more than 30km, the length of the flying space is at least 6 hours, but the overpressure balloons are in the form of hanging load cabins under one giant overpressure balloon, and the development cost of the overpressure balloons is extremely high, and the development period is also long.
The French CNES high-altitude balloon mechanism has been successfully tested to fly for 6 times of overpressure balloon test flight experiments with the task names of CLIMAT, BANA, PLOT and the like, the weight-bearing capacity is more than 200kg, the flying height is more than 30km, and a mode of hanging an auxiliary balloon under a main overpressure balloon is adopted.
The success of the photoelectric hospital of Chinese academy of sciences in 2017 is up to 25km, and the overpressure balloon with the load of 300kg is adopted in the form of a load cabin mounted under a giant overpressure balloon.
All the mechanisms have successfully completed the transportation of loads of more than 100 kilograms to the adjacent space with the altitude of more than 20km and have short-term parking, but all the mechanisms adopt the overpressure balloon technology, and the overpressure balloon is very expensive in manufacturing cost, extremely high in research and development cost, long in research and development period, complex in issuing facilities and high in requirements on issuing personnel.
Regarding the high-altitude balloon issuing method, Wanglixiang et al, the institute of high-energy physics of Chinese academy, discloses a high-altitude balloon issuing method, which issues balloons by operating a winch in combination with a releaser mounted on the balloons, and raises the balloons for a certain distance when the wind speed is high, so that the instrument cabin is not lifted.
Zhang Taihua et al, an aerospace information innovation research institute of Chinese academy, discloses a high-altitude balloon delivery system and method, which can deliver a pod and a load of a high-altitude balloon without impact, but when the wind speed is high and the volume of the balloon is large, the balloon is blown onto a first restraint device, and the friction between the restraint device and the balloon can cause great damage to the skin of the balloon.
A novel large-size high-altitude balloon release mode is disclosed by Maryunpeng et al of Beijing aerospace university, and a windproof method of the novel large-size high-altitude balloon release mode is characterized in that a plurality of windproof ropes capable of releasing length are connected around the high-altitude balloon, the windproof ropes are used for pulling the balloon when wind is strong to prevent the balloon from swinging too large, and the windproof measures still cannot inflate the balloon and finish flying when the wind is strong.
Disclosure of Invention
One of the purposes of the invention is to provide a combined type high-load high-altitude floating test platform with low cost and simple structure, so as to solve the problems of low load capacity and high manufacturing cost of the existing high-altitude floating test platform; the second purpose is to provide a method for rapidly flying the test platform under the condition of large wind power.
The invention provides a combined type large-load high-altitude floating test platform which comprises a main zero-pressure ball, a plurality of auxiliary zero-pressure balls, a main cable, a plurality of auxiliary cables and a load cabin, wherein the main zero-pressure ball is arranged on the main cable; the ball handle is connected with a main cable after the main zero-pressure ball is inflated, and the load cabin is connected with the lower end of the main cable; one end of each of the auxiliary cables is connected to the main cable at a designed interval; after each auxiliary zero-pressure ball is inflated, the ball handle of each auxiliary zero-pressure ball is connected with the other end of one auxiliary cable; after the test platform is lifted off, the main zero-pressure balloon is positioned at the uppermost end, and the main zero-pressure balloon is not in contact with the auxiliary zero-pressure balloon and the auxiliary zero-pressure balloon.
In one embodiment of the above test platform, the diameter of the main zero-pressure ball is larger than the diameter of the auxiliary zero-pressure ball.
In one embodiment of the above test platform, the auxiliary cables are alternately arranged on the left side and the right side of the adjacent connecting nodes on the main cable.
The windproof fixing assembly before flying of the test platform comprises a U-shaped enclosure fixed on the ground, a cable node fixing piece and a fixed pulley, wherein the height of the U-shaped enclosure is not less than the total height of the auxiliary zero-pressure ball and the auxiliary cable, the cable node fixing piece is arranged along the central plane of the width of the opening of the U-shaped enclosure, and the fixed pulley is positioned at the opening of the U-shaped enclosure.
In one embodiment of the above wind-proof fixing assembly, the cable node fixing member is a synchronous releasing mechanism, and the synchronous releasing mechanism is provided with the same number of clamps as the number of cable nodes.
The invention provides a method for positioning the test platform in the windproof fixing component, which comprises the following steps:
(1) auxiliary cables are connected to the main cable at set intervals
One end of each auxiliary cable rope is connected and fixed at a designated position on the main cable rope in sequence, and adjacent connecting nodes are respectively positioned at the left side and the right side of the main cable rope, so that each auxiliary zero-pressure ball floats on the main cable rope and is connected in series in a tree shape;
(2) limiting the connecting nodes of the main cable and each auxiliary cable respectively through cable node fixing pieces;
(3) connecting the main zero-pressure ball to the inner end of the main cable after inflating the main zero-pressure ball, so that the main zero-pressure ball is positioned at the innermost end of the U-shaped enclosure inner cavity;
(4) respectively inflating each auxiliary zero-pressure ball and then connecting the auxiliary zero-pressure ball to the upper end of each auxiliary cable rope to enable each auxiliary zero-pressure ball to be positioned in a U-shaped enclosure in a row;
(5) an adjusting rope and a load cabin connecting rope are connected at an auxiliary cable connecting node at the outermost end of the main cable, the adjusting rope is wound on the fixed pulley, and the load cabin is fixedly connected with the load cabin connecting rope;
so far, all inflated zero-pressure balls of the test platform are surrounded by the U-shaped barrier frame and fixed through the synchronous release mechanism, and then can be released.
The invention provides a flying method of a test platform in the windproof fixing component, which comprises the following steps:
(1) simultaneously opening the cable node fixing piece to lift all the zero-pressure balls, pulling the adjusting rope when the zero-pressure balls are lifted, and rotating the fixed pulley until the adjusting rope is straightened and the load cabin is lifted off;
(2) cutting off the adjusting rope and flying the test platform.
The invention adopts a small zero pressure ball combination mode to finish high-altitude load flying, and the manufacturing cost of the zero pressure ball is lower, so the test cost is greatly reduced. The windproof fixing device arranged on the ground is simple in structure and configuration, convenient to operate, low in requirement on test sites, and few in required staff when the test platform is flown. And releasing the load after the test platform reaches the task altitude, and rapidly ascending the zero-pressure balloon to the maximum altitude for blasting without the problem of subsequent flight airspace.
Drawings
Fig. 1 is an enlarged schematic view of a test platform according to an embodiment of the present invention in a fixed state on the ground before flying (the load chamber is not shown).
FIG. 2 is a schematic right-view reduced view of the test platform of FIG. 1.
Fig. 3 is a schematic view of the test platform flying process.
Fig. 4 is a schematic view of the airborne state of the experimental platform after flying.
Detailed Description
As can be seen from fig. 1 to 4, the combined high-load high-altitude floating test platform disclosed in this embodiment includes a main zero-pressure ball 1, a main cable 2, an auxiliary zero-pressure ball 3, an auxiliary cable 4, and a load compartment 5.
The diameter of the main zero-pressure ball 1 is larger than that of the auxiliary zero-pressure ball 3, one main zero-pressure ball is positioned at the uppermost end of the test platform after being lifted, the inflation amount is the largest of all the balloons, and the inflation amount is optimally determined by the weight of the task load.
After the main zero-pressure ball 1 is inflated, a main cable 2 is connected to the ball handle, and the main cable 2 bears the maximum stress in the test platform and has the longest length. Therefore, the main cable is made of a cable material with lower density and better tensile strength, such as: the main rope can be selected to be made of F-12 fibers with the linear density of 130tex, every two bundles of the main rope are twisted into a rope blank, and then three rope blanks are twisted into a rope. The tensile strength value of the rope manufactured by the method is about 1800N, the performance is not changed within the range of the using temperature of minus 50 ℃ to plus 40 ℃, the diameter is about 1mm, and the linear density is about 0.8 g/m.
The main mooring rope 2 is sequentially connected with the auxiliary mooring ropes 4 along the length direction, namely the lower ends of the auxiliary mooring ropes 4 are sequentially connected with the designated positions on the main mooring rope 2, and the connected adjacent nodes are respectively positioned on the left side and the right side of the main mooring rope 2.
The number of auxiliary cables 4 is the same as the number of auxiliary zero-pressure balls 3, nine auxiliary zero-pressure balls 3 being shown in fig. 2.
This example uses hydrogen as the buoyant gas.
The distance between the connecting nodes of the auxiliary cables 4 on the main cable 2 is determined by the condition that the top end of each auxiliary zero-pressure ball 3 does not contact the bottom end of the auxiliary zero-pressure ball above the auxiliary zero-pressure ball after being lifted.
Because the auxiliary zero-pressure balls contact with the main cable and/or the auxiliary cable to generate friction in the process of lifting the test platform, in order to avoid damage caused by friction between the auxiliary zero-pressure balls and the cable, the surfaces of the auxiliary zero-pressure balls, the main cable and the auxiliary cable need to be subjected to smoothness treatment.
Before the test platform flies, the test platform needs to be inflated and fixed on the ground, and because the diameter of each zero-pressure ball is large, and after all the zero-pressure balls are inflated, the total volume of the test platform is large, the wind resistance is large, and therefore in order to avoid the influence of the inflated wind resistance, a fixing device is arranged on the ground during inflation.
Prevent wind fixed subassembly and include that the U type encloses fender 6, hawser node mounting 7 and take the fixed pulley 8 of mounting bracket, and the U type encloses the lower extreme that keeps off 6 and is fixed in subaerially.
The height of the U-shaped enclosure 6 is at least flush with the highest point of the main zero-pressure ball 1 after inflation and fixation, the length of the U-shaped enclosure can ensure that all the zero-pressure balls are located in the inner cavity of the U-shaped enclosure after inflation, and the width of the U-shaped enclosure is slightly larger than the diameter of the main zero-pressure ball so that the main zero-pressure ball can be smoothly released.
The auxiliary zero-pressure balls 3 are respectively connected with the auxiliary cables 4 after being inflated, and the lower ends of the auxiliary cables 4 are respectively fixed on the main cable 2, so that the auxiliary cable connecting nodes on the main cable 2 are required to be fixed to fix the auxiliary zero-pressure balls.
In the embodiment, the cable node fixing element 7 adopts a synchronous release mechanism disclosed in CN111824383A, the specific structure and application of the mechanism are described in the specification and drawings of the specification, and the number of clamps of the mechanism is set to be the same as that of all balloons.
The synchronous release mechanism is fixed along the central plane of the width of the U-shaped enclosure opening.
The fixed pulley 8 is arranged at the opening of the U-shaped enclosure.
The cable node fixing piece of other embodiments can also adopt outsourcing piece electric control buckles, the electric control buckles with the same quantity as the auxiliary zero-pressure balls are fixed on the ground, and all the electric control buckles are opened simultaneously through the remote control switch when the cable node fixing piece is released.
The processes of inflation of each zero-pressure ball of the test platform and fixation in the windproof fixing component are as follows:
(1) the main cable is connected with auxiliary cables according to a set interval.
One end of each auxiliary cable rope is connected and fixed at a designated position on the main cable rope in sequence, and adjacent connecting nodes are respectively positioned at the left side and the right side of the main cable rope, so that each auxiliary zero-pressure ball floats on the main cable rope to form dendritic series connection.
(2) And clamping the connecting nodes of the main cable and each auxiliary cable respectively through a clamp of the synchronous release mechanism.
(3) And the main zero-pressure ball is inflated and then connected to the inner end of the main cable, so that the main zero-pressure ball is positioned at the innermost end of the U-shaped enclosure inner cavity.
(4) And respectively inflating each auxiliary zero-pressure ball and then connecting the auxiliary zero-pressure ball to the upper end of each auxiliary cable, so that each auxiliary zero-pressure ball is positioned in the U-shaped enclosure in a row.
(5) An adjusting rope and a load cabin connecting rope are connected at an auxiliary rope connecting node at the outermost end of the main rope, the adjusting rope is wound on the fixed pulley, and the load cabin connecting rope are fixedly connected.
So far, all inflated zero-pressure balls of the test platform are surrounded by the U-shaped barrier frame and fixed through the synchronous release mechanism, and then can be released.
When the floating system flies, the clamps of the synchronous release mechanism are opened simultaneously, all the zero-pressure balls are not restrained, the main zero-pressure ball is largest in volume and buoyancy, the test platform is in the state shown in fig. 3 under the traction of the main zero-pressure ball, at the moment, the lift force of the test platform mainly acts on the adjusting rope, if no special condition exists, the adjusting rope is slowly released until the load is lifted off the ground, the adjusting rope is cut off, the test platform flies integrally, all the auxiliary zero-pressure balls are connected in series on the main cable in a tree-like mode, the buoyancy of the main zero-pressure ball is much larger than that of other zero-pressure balls, and the heavier load cabin below the main zero-pressure ball provides downward tension, so that the whole floating system can maintain the shape in the flying process until the target altitude is reached, and the floating system is temporarily parked as shown in fig. 4.
Through verification, at the altitude of zero, 1kg of hydrogen is only filled into the auxiliary zero-pressure balls, the diameter of the auxiliary zero-pressure balls after expansion is 3m, the net lifting force of each auxiliary zero-pressure ball is 11.8kg, the maximum flight height is 20km above the altitude, and a task load with the weight of 200kg can be temporarily stopped at the altitude of 20km after the task load needs about 20 auxiliary zero-pressure balls to perform dendritic series lifting.
The invention has the following advantages:
1. the high-altitude load flying is completed by adopting a small zero-pressure ball combination mode, and the manufacturing cost of the zero-pressure ball is low, so the experiment cost is greatly reduced.
2. The buoyancy lifting gas adopts hydrogen, the potential safety hazard of outdoor flying is very small, and the flying cost is further reduced.
3. The windproof fixed component is simple in configuration, convenient to operate, low in requirement on test sites, and few in required flying test personnel.
4. And releasing the load after the test platform reaches the task altitude, and rapidly ascending the zero-pressure balloon to the maximum altitude for blasting without the problem of subsequent flight airspace.
Claims (7)
1. The utility model provides a modular big load high altitude test platform that floats, its characterized in that: the device comprises a main zero-pressure ball, a plurality of auxiliary zero-pressure balls, a main cable, a plurality of auxiliary cables and a load cabin;
the ball handle is connected with a main cable after the main zero-pressure ball is inflated, and the load cabin is connected with the lower end of the main cable;
one end of each of the auxiliary cables is connected to the main cable at a designed interval;
after each auxiliary zero-pressure ball is inflated, the ball handle of each auxiliary zero-pressure ball is connected with the other end of one auxiliary cable;
after the test platform is lifted off, the main zero-pressure ball is positioned at the uppermost end, and the main zero-pressure ball is not in contact with the auxiliary zero-pressure ball and the auxiliary zero-pressure ball.
2. The combined large-load high-altitude floating test platform as claimed in claim 1, wherein: the diameter of the main zero-pressure ball is larger than that of the auxiliary zero-pressure ball.
3. The combined large-load high-altitude floating test platform as claimed in claim 2, wherein: the adjacent connecting nodes of the auxiliary cables on the main cable are alternately arranged according to the left side and the right side.
4. A wind-resistant mounting assembly for use before flying a test platform according to claim 3, wherein: it encloses fender, hawser node mounting and fixed pulley including being fixed in subaerial U type, and the height that the fender was enclosed to the U type is not less than the total height of supplementary zero-pressure ball and supplementary hawser, hawser node mounting enclose the central plane of keeping off opening width along the U type and arrange, and the fixed pulley is located the opening part that the fender was enclosed to the U type.
5. The wind resistant fixing assembly of claim 4 wherein: the cable node fixing piece is a synchronous releasing mechanism, and the synchronous releasing mechanism is provided with clamps the number of which is the same as that of the cable nodes.
6. A method of positioning a test platform as claimed in claim 5 in a wind-resistant mounting assembly as claimed in claim 4, comprising the steps of:
(1) auxiliary cables are connected to the main cable at set intervals
One end of each auxiliary cable rope is connected and fixed at a designated position on the main cable rope in sequence, and adjacent connecting nodes are respectively positioned at the left side and the right side of the main cable rope, so that each auxiliary zero-pressure ball floats on the main cable rope and is connected in series in a tree shape;
(2) limiting the connecting nodes of the main cable and each auxiliary cable respectively through cable node fixing pieces;
(3) connecting the main zero-pressure ball to the inner end of the main cable after inflating the main zero-pressure ball, so that the main zero-pressure ball is positioned at the innermost end of the U-shaped enclosure inner cavity;
(4) respectively inflating each auxiliary zero-pressure ball and then connecting the auxiliary zero-pressure ball to the upper end of each auxiliary cable rope to enable each auxiliary zero-pressure ball to be positioned in a U-shaped enclosure in a row;
(5) an adjusting rope and a load cabin connecting rope are connected at an auxiliary cable connecting node at the outermost end of the main cable, the adjusting rope is wound on the fixed pulley, and the load cabin is fixedly connected with the load cabin connecting rope;
so far, all inflated zero-pressure balls of the test platform are surrounded by the U-shaped barrier frame and fixed through the synchronous release mechanism, and then can be released.
7. A method of flying said test platform in said wind resistant mounting assembly of claim 6, including the steps of:
(1) simultaneously opening the cable node fixing piece to lift all the zero-pressure balls, pulling the adjusting rope when the zero-pressure balls are lifted, and rotating the fixed pulley until the adjusting rope is straightened and the load cabin is lifted off;
(2) cutting off the adjusting rope and flying the test platform.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110441982.8A CN113022839B (en) | 2021-04-23 | 2021-04-23 | Combined type large-load high-altitude floating test platform and flying method thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110441982.8A CN113022839B (en) | 2021-04-23 | 2021-04-23 | Combined type large-load high-altitude floating test platform and flying method thereof |
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| Publication Number | Publication Date |
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| CN113022839A true CN113022839A (en) | 2021-06-25 |
| CN113022839B CN113022839B (en) | 2022-10-14 |
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Citations (5)
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|---|---|---|---|---|
| GB1097097A (en) * | 1965-03-24 | 1967-12-29 | George Ingram | Improvements in or relating to balloon apparatus for load carrying |
| CN106005350A (en) * | 2016-05-19 | 2016-10-12 | 东莞前沿技术研究院 | Flying method for large balloon |
| CN206344984U (en) * | 2016-12-30 | 2017-07-21 | 中国科学院光电研究院 | A kind of stratosphere is tethered at aerostatics platform |
| CN111547227A (en) * | 2020-04-02 | 2020-08-18 | 中国科学院空天信息创新研究院 | Method for issuing ultra-high altitude mooring aerostat |
| CN111746774A (en) * | 2020-06-01 | 2020-10-09 | 中国科学院空天信息创新研究院 | High-altitude balloon issuing system and method |
-
2021
- 2021-04-23 CN CN202110441982.8A patent/CN113022839B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1097097A (en) * | 1965-03-24 | 1967-12-29 | George Ingram | Improvements in or relating to balloon apparatus for load carrying |
| CN106005350A (en) * | 2016-05-19 | 2016-10-12 | 东莞前沿技术研究院 | Flying method for large balloon |
| US20190054994A1 (en) * | 2016-05-19 | 2019-02-21 | Dongguan Frontier Technology Institute | Method for flying large balloon |
| CN206344984U (en) * | 2016-12-30 | 2017-07-21 | 中国科学院光电研究院 | A kind of stratosphere is tethered at aerostatics platform |
| CN111547227A (en) * | 2020-04-02 | 2020-08-18 | 中国科学院空天信息创新研究院 | Method for issuing ultra-high altitude mooring aerostat |
| CN111746774A (en) * | 2020-06-01 | 2020-10-09 | 中国科学院空天信息创新研究院 | High-altitude balloon issuing system and method |
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| CN113022839B (en) | 2022-10-14 |
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