CN216035059U - High-altitude weight reduction device of stratospheric aircraft - Google Patents
High-altitude weight reduction device of stratospheric aircraft Download PDFInfo
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- CN216035059U CN216035059U CN202122534305.9U CN202122534305U CN216035059U CN 216035059 U CN216035059 U CN 216035059U CN 202122534305 U CN202122534305 U CN 202122534305U CN 216035059 U CN216035059 U CN 216035059U
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- box body
- electromagnet
- feed opening
- weight reduction
- reduction device
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Abstract
The utility model discloses a high-altitude weight reducing device of a stratospheric aircraft, which comprises an upper box body, a lower box body, a command controller and an electromagnet assembly, wherein the upper box body is arranged above the lower box body, the upper box body and the lower box body are both arranged in a hollow manner, the upper box body is used for accommodating a balance weight, the bottom of the lower box body is provided with a feed opening communicated with the upper box body, the electromagnet assembly is arranged at the feed opening, the electromagnet assembly is electrically connected with the command controller, and the command controller is used for controlling the electromagnet assembly to operate and opening or closing the feed opening. The high-altitude weight reducing device of the stratospheric aircraft has the advantages of light weight, high safety and simple structure.
Description
Technical Field
The utility model relates to the technical field of stratospheric aircrafts, in particular to a high-altitude weight reducing device of a stratospheric aircraft.
Background
In recent years, various stratospheric aircrafts are being researched by various countries. The stratospheric airship is a novel low-cost and low-energy-consumption stratospheric aircraft, the requirement on the total weight control of the stratospheric airship by a high-altitude weight reduction device is very strict, and the weight reduction device generally causes weight reduction material agglomeration or control failure at high altitude due to low temperature, so that the airship cannot reduce weight, and the current aerospace requirement cannot be met.
At present, there is a need for a high altitude weight reducing device for a stratospheric aircraft.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a high-altitude weight reducing device of a stratospheric aircraft, which is light in weight, high in safety and simple in structure.
In order to achieve the purpose, the high-altitude weight reducing device of the stratosphere aircraft comprises an upper box body, a lower box body, a command controller and an electromagnet assembly, wherein the upper box body is arranged above the lower box body, the upper box body and the lower box body are both arranged in a hollow mode, the upper box body is used for accommodating a balance weight, a feed opening communicated with the upper box body is formed in the bottom of the lower box body, the electromagnet assembly is arranged at the feed opening, the electromagnet assembly is electrically connected with the command controller, and the command controller is used for controlling the electromagnet assembly to operate and enabling the feed opening to be opened or closed.
Preferably, the upper box body is of a cuboid structure.
Preferably, the lower box body is of a prismatic table structure.
Preferably, the electromagnet assembly comprises an electromagnet and an electric door, the electromagnet is sleeved outside the feed opening, the electric door is movably arranged on the feed opening, and the electric door is driven by the electromagnet to move and open or close the feed opening.
Specifically, the electromagnet assembly further comprises an electromagnet protection box and a connecting arm, the electromagnet protection box is arranged in the electromagnet, and the electromagnet protection box is connected with the lower box body through the connecting arm.
Specifically, the connecting arms are symmetrically arranged.
Preferably, the lower box body extends downwards to form a discharge pipe, and the feed opening is formed in the discharge pipe.
Preferably, the high-altitude weight reducing device of the stratospheric aircraft further comprises a safety device for preventing the feed opening from being blocked.
Preferably, the safety device is provided with an electric detonator.
Compared with the prior art, the stratospheric aircraft high-altitude weight reducing device of the utility model combines an upper box body, a lower box body, a command controller, an electromagnet assembly and the like together, wherein the upper box body is arranged above the lower box body, the upper box body and the lower box body are both arranged in a hollow manner, the upper box body is used for accommodating a balance weight, the bottom of the lower box body is provided with a feed opening communicated with the upper box body, the feed opening is provided with the electromagnet assembly, the electromagnet assembly is electrically connected with the command controller, the command controller is used for controlling the electromagnet assembly to operate and opening or closing the feed opening, thereby achieving the aim of feeding, the electromagnet assembly is arranged to ensure that the stratospheric aircraft high-altitude weight reducing device is convenient to control and simple in structure, the viability of the aircraft is greatly improved, moreover, the weight reducing effect on a stratospheric airship is greatly improved through the control of the electromagnet assembly, the anti-interference capability on the environment is strong, even at low temperature, the phenomenon of control failure or weight loss and agglomeration can not occur.
Drawings
Fig. 1 is a schematic perspective structure diagram of the high-altitude weight-reducing device of the stratospheric aircraft.
Fig. 2 is a schematic perspective view of another angle of the high altitude weight reducing device of the stratospheric aircraft.
Fig. 3 is a schematic perspective view of another angle of the high altitude weight reducing device of the stratospheric aircraft.
Fig. 4 is a schematic plan structure view of the high-altitude weight-reducing device of the stratospheric aircraft in the front view direction.
Detailed Description
In order to explain technical contents, structural features, and effects achieved by the present invention in detail, the following detailed description is given with reference to the embodiments and the accompanying drawings.
Referring to fig. 1 to 4, the utility model provides an overhead weight reducing device 100 for a stratospheric aircraft, which comprises an upper box body 1, a lower box body 2, a command controller 3 and an electromagnet assembly 4, wherein the upper box body 1 is arranged above the lower box body 2, the upper box body 1 and the lower box body 2 are both arranged in a hollow manner, the upper box body 1 and the lower box body 2 are both alloy box bodies, the upper box body 1 is used for accommodating a counterweight, the bottom of the lower box body 2 is provided with a feed opening 21 communicated with the upper box body 1, the electromagnet assembly 4 is arranged at the feed opening 21, the electromagnet assembly 4 is electrically connected with the command controller 3, the command controller 3 is used for controlling the electromagnet assembly 4 to operate and opening or closing the feed opening 21, so as to achieve the purpose of discharging, the arrangement of the electromagnet assembly 4 enables the overhead weight reducing device 100 for the stratospheric aircraft to be convenient to control, the structure to be simple, and the viability of the aircraft to be greatly improved, moreover, the weight reduction effect of the stratospheric airship is greatly improved through the control of the electromagnet assembly 4, the unloading speed and the unloading amount are flexibly controlled, the environment anti-interference capacity is strong, and the phenomenon of control failure or weight reduction material agglomeration cannot occur even at low temperature. Preferably, the upper box 1 is a rectangular parallelepiped structure, the lower box 2 is a prismoid structure, the bottom of the prismoid structure is 150 degrees, and the arrangement of 150 degrees can prevent the weight-reduced materials from being extruded to form the material blocking, but not limited thereto. More specifically, the following:
referring to fig. 4, the lower housing 2 extends downward to form a discharge pipe 22, and the discharge port 21 is disposed on the discharge pipe 22.
Referring to fig. 1 to 4, the electromagnet assembly 4 includes an electromagnet 41, an electric door 42, an electromagnet protecting box 43 and a connecting arm 44, the electromagnet 41 is sleeved outside the feeding opening 21, the electric door 42 is movably disposed on the feeding opening 21, and the electric door 42 moves under the driving of the electromagnet 41 and opens or closes the feeding opening 21. The electromagnet 41 is built in an electromagnet protection box 43, the electromagnet protection box 43 has a through hole for the discharge pipe 22 to pass through, and the electromagnet protection box 43 is connected with the lower case 2 through a connecting arm 44. Preferably, the connecting arms 44 are symmetrically disposed, but not limited thereto.
Referring to fig. 1 to 4, the high altitude weight reducing device 100 of the stratospheric aircraft of the present invention further includes a safety device (not shown) for preventing the feed opening 21 from being locked. The safety device is provided with an electronic detonator which ensures the discharge pipe 22 to be smooth, and once the discharge pipe is blocked, the counterweight can be removed through the safety device.
In summary, referring to fig. 1 to 4, a detailed description is made of the production process of the stratospheric aircraft high altitude weight reduction device 100 of the present invention:
subtract heavy device 100 and stratosphere airship with stratosphere aircraft high altitude and be connected fixedly, subtract heavy material to the stratosphere airship of known buoyancy with certain weight, fly along with the airship, finally stabilize on the high altitude of needs, when the airship stops in the sky a period, because various reasons will lead to airship buoyancy to reduce, can subtract heavy device 100 through stratosphere aircraft high altitude at this time, reduce the weight of airship, continue to let the airship stabilize in the sky, increase the dwell time of airship, thereby improve the viability of airship, concrete control operation: the ground communication monitoring system through the airship monitors the flying height of the airship in real time, when the airship is found to have a descending trend, the command controller 3 connected through the radio sends an instruction to drive the electromagnet assembly 4 to work, the weight reducing material is released, and when the airship is stabilized to a corresponding height again, the command controller 3 controls the electromagnet assembly 4 to stop working. Finally, the airship is stabilized.
The upper box body 1 is arranged above the lower box body 2, the upper box body 1 and the lower box body 2 are both arranged in a hollow mode, the upper box body 1 is used for containing a balance weight, the bottom of the lower box body 2 is provided with a feed opening 21 communicated with the upper box body 1, the electromagnet assembly 4 is arranged at the feed opening 21, the electromagnet assembly 4 is electrically connected with the command controller 3, the command controller 3 is used for controlling the electromagnet assembly 4 to operate and opening or closing the feed opening 21, so that the aim of feeding is achieved, the electromagnet assembly 4 is arranged to enable the high-altitude weight reducing device 100 of the stratosphere aircraft to be convenient to control and simple in structure, the viability of the aircraft is greatly improved, the weight reducing effect of the stratosphere airship is greatly improved through the control of the electromagnet assembly 4, and the anti-jamming capability to the environment is strong, even at low temperature, the phenomenon of control failure or weight loss and agglomeration can not occur.
The above disclosure is only a preferred embodiment of the present invention, and certainly should not be taken as limiting the scope of the present invention, which is therefore intended to cover all equivalent changes and modifications within the scope of the present invention.
Claims (10)
1. The high-altitude weight reducing device of the stratospheric aircraft is characterized by comprising an upper box body, a lower box body, a command controller and an electromagnet assembly, wherein the upper box body is installed above the lower box body, the upper box body and the lower box body are arranged in a hollow mode, the upper box body is used for accommodating a balance weight, a feed opening communicated with the upper box body is formed in the bottom of the lower box body, the electromagnet assembly is arranged at the feed opening, and the electromagnet assembly is electrically connected with the command controller, and is used for controlling the electromagnet assembly to run and enable the feed opening to be opened or closed.
2. The stratospheric aircraft high altitude weight reduction device of claim 1, wherein the upper box is of a rectangular parallelepiped structure.
3. The stratospheric aircraft high altitude weight reduction device of claim 1, wherein the lower box is of a prismoid structure.
4. The stratospheric aircraft high altitude weight reduction device of claim 3, wherein the base of the frustum of pyramid structure is at 150 degrees.
5. The stratospheric aircraft high altitude weight reduction device according to claim 1, wherein the electromagnet assembly comprises an electromagnet and an electric door, the electromagnet is sleeved outside the feed opening, the electric door is movably arranged at the feed opening, and the electric door is driven by the electromagnet to move and open or close the feed opening.
6. The stratospheric aircraft high altitude weight reduction device according to claim 5, wherein the electromagnet assembly further comprises an electromagnet protection box and a connecting arm, the electromagnet is arranged in the electromagnet protection box, and the electromagnet protection box is connected with the lower box body through the connecting arm.
7. The stratospheric aircraft high altitude weight reduction device of claim 6, wherein the connecting arms are symmetrically arranged.
8. The stratospheric aircraft high altitude weight reduction device of claim 1, wherein the lower tank body extends downward to form a discharge pipe, and the feed opening is formed in the discharge pipe.
9. The stratospheric aircraft high altitude weight reduction device of claim 1, further comprising a safety device for preventing the feed opening from being stuck.
10. A stratospheric aircraft high altitude weight reduction device as claimed in claim 9, wherein said safety device is provided with an electric squib.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122534305.9U CN216035059U (en) | 2021-10-20 | 2021-10-20 | High-altitude weight reduction device of stratospheric aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122534305.9U CN216035059U (en) | 2021-10-20 | 2021-10-20 | High-altitude weight reduction device of stratospheric aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN216035059U true CN216035059U (en) | 2022-03-15 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202122534305.9U Active CN216035059U (en) | 2021-10-20 | 2021-10-20 | High-altitude weight reduction device of stratospheric aircraft |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11613364B2 (en) | 2013-02-22 | 2023-03-28 | World View Enterprises Inc. | Near-space operation systems |
| US11904999B2 (en) | 2017-01-09 | 2024-02-20 | World View Enterprises Inc. | Lighter than air balloon systems and methods |
-
2021
- 2021-10-20 CN CN202122534305.9U patent/CN216035059U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11613364B2 (en) | 2013-02-22 | 2023-03-28 | World View Enterprises Inc. | Near-space operation systems |
| US11904999B2 (en) | 2017-01-09 | 2024-02-20 | World View Enterprises Inc. | Lighter than air balloon systems and methods |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20221025 Address after: Room 1101, 11th floor, College International Building, No. 1, Zhichun Road, Haidian District, Beijing 100083 Patentee after: Iridium gasman Aviation Technology Group Co.,Ltd. Address before: 523000 Room 201, building 6, No.4 Xingye Road, Songshanhu Park, Dongguan City, Guangdong Province Patentee before: Dongguan Lingkong Remote Sensing Technology Co.,Ltd. |