CN109398672B - Liquid bidirectional pump system and stratospheric airship attitude adjusting device adopting same - Google Patents
Liquid bidirectional pump system and stratospheric airship attitude adjusting device adopting same Download PDFInfo
- Publication number
- CN109398672B CN109398672B CN201811351590.7A CN201811351590A CN109398672B CN 109398672 B CN109398672 B CN 109398672B CN 201811351590 A CN201811351590 A CN 201811351590A CN 109398672 B CN109398672 B CN 109398672B
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- liquid
- pump system
- stratospheric airship
- tank
- electromagnetic valve
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- 239000007788 liquid Substances 0.000 title claims abstract description 207
- 230000002457 bidirectional effect Effects 0.000 title claims abstract description 17
- 238000004891 communication Methods 0.000 claims description 18
- 230000002528 anti-freeze Effects 0.000 claims description 12
- 238000001802 infusion Methods 0.000 claims description 7
- 230000000694 effects Effects 0.000 claims description 5
- 238000009423 ventilation Methods 0.000 claims description 3
- 238000010586 diagram Methods 0.000 description 8
- 238000000034 method Methods 0.000 description 7
- 230000036544 posture Effects 0.000 description 7
- 108010066114 cabin-2 Proteins 0.000 description 6
- 239000005437 stratosphere Substances 0.000 description 6
- 239000003570 air Substances 0.000 description 5
- 230000005484 gravity Effects 0.000 description 5
- 239000004576 sand Substances 0.000 description 5
- 230000006978 adaptation Effects 0.000 description 3
- 239000012080 ambient air Substances 0.000 description 2
- 238000009835 boiling Methods 0.000 description 2
- 239000002775 capsule Substances 0.000 description 2
- JEIPFZHSYJVQDO-UHFFFAOYSA-N iron(III) oxide Inorganic materials O=[Fe]O[Fe]=O JEIPFZHSYJVQDO-UHFFFAOYSA-N 0.000 description 2
- 238000013461 design Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 230000003252 repetitive effect Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/06—Rigid airships; Semi-rigid airships
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/06—Rigid airships; Semi-rigid airships
- B64B1/22—Arrangement of cabins or gondolas
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04C—ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT PUMPS
- F04C15/00—Component parts, details or accessories of machines, pumps or pumping installations, not provided for in groups F04C2/00 - F04C14/00
- F04C15/06—Arrangements for admission or discharge of the working fluid, e.g. constructional features of the inlet or outlet
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04C—ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT PUMPS
- F04C2/00—Rotary-piston machines or pumps
- F04C2/08—Rotary-piston machines or pumps of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing
- F04C2/12—Rotary-piston machines or pumps of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing of other than internal-axis type
- F04C2/14—Rotary-piston machines or pumps of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing of other than internal-axis type with toothed rotary pistons
- F04C2/18—Rotary-piston machines or pumps of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing of other than internal-axis type with toothed rotary pistons with similar tooth forms
Abstract
The invention provides a liquid bidirectional pump system and a stratospheric airship posture adjusting device adopting the same. The liquid bi-directional pump system has a first end and a second end, including a gear pump system and first through fourth solenoid valves, wherein: the first end of the liquid bi-directional pump system, the first end of the first solenoid valve and the first end of the fourth solenoid valve are communicated; the second end of the first electromagnetic valve, the inlet of the gear pump system and the first end of the third electromagnetic valve are communicated; the second end of the fourth electromagnetic valve, the outlet of the gear pump system and the first end of the second electromagnetic valve are communicated; and a second end of the third solenoid valve, a second end of the second solenoid valve, and a second end of the liquid bi-directional pump system. The stratospheric airship attitude adjusting device adopting the liquid bi-directional pump system changes the centroid and the pitching attitude of the stratospheric airship by changing the mass of liquid in the end liquid storage cabin.
Description
Technical Field
The invention relates to the technical field of airship, in particular to a liquid bidirectional pump system and a stratospheric airship posture adjusting device adopting the same.
Background
For a general airship, the pitching attitude angle of the airship can be adjusted by controlling the control surface of the tail wing; or the windward angle of the control surface of the tail wing is changed, so that the tail wing generates power in the pitching direction, and the purpose of adjusting the pitching attitude angle of the airship is achieved.
However, due to the low ambient air density in the stratosphere, the rudder performance of the tail control surface is not great and useless weight is increased when the stratospheric airship is designed to fly at an altitude of 20 km at an airspeed of less than 20 meters per second. Therefore, the tail fin control surface is not suitable for the stratospheric airship.
In addition, at low altitude, the mass center of the airship can be changed by adjusting the mass of the air ballonets at the two ends of the airship due to the large air density.
However, due to the low ambient air density of the stratosphere and the over-temperature and over-pressure within the stratosphere airship formed by solar radiation heat, all the air within the airship will be exhausted during the day when the stratosphere airship is designed. Therefore, the method for changing the mass center of the airship and adjusting the pitching attitude of the airship by adjusting the air quality of the auxiliary air bags at the head end and the tail end of the airship is difficult to realize.
In addition, by adopting the method of changing the mass center and adjusting the pitching attitude of the stratospheric airship by throwing sand at the two ends of the airship, the sand is thrown more and less, and the airship cannot be recycled.
How to effectively adjust the centroid and pitch attitude angle of a stratospheric airship in a stratospheric environment is a key issue for the overall design of the stratospheric airship.
Therefore, designing a novel stratospheric airship attitude adjusting device is a technical problem to be solved at present.
Disclosure of Invention
The present invention is directed to a stratospheric airship attitude adjustment device that, at least in part, overcomes one or more of the problems due to the limitations and disadvantages of the related art.
Other features and advantages of the invention will be apparent from the following detailed description, or may be learned by the practice of the invention.
According to a first aspect of the present invention, a liquid bi-directional pump system is disclosed having a first end and a second end, the liquid bi-directional pump system comprising a gear pump system and first to fourth solenoid valves, wherein:
the first end of the liquid bi-directional pump system, the first end of the first solenoid valve and the first end of the fourth solenoid valve are communicated;
the second end of the first electromagnetic valve, the inlet of the gear pump system and the first end of the third electromagnetic valve are communicated;
the second end of the fourth electromagnetic valve, the outlet of the gear pump system and the first end of the second electromagnetic valve are communicated; and
the second end of the third solenoid valve, the second end of the second solenoid valve, and the second end of the liquid bi-directional pump system are in communication.
According to an exemplary embodiment of the invention, the communication takes place through an infusion line.
According to an exemplary embodiment of the invention, wherein the gear pump system, the third solenoid valve and the fourth solenoid valve are simultaneously opened and the first solenoid valve and the second solenoid valve are simultaneously closed when liquid is required to flow from the second end to the first end; when liquid is required to flow from the first end to the second end, the gear pump system, the first electromagnetic valve and the second electromagnetic valve are simultaneously opened, and the third electromagnetic valve and the fourth electromagnetic valve are simultaneously closed.
According to a second aspect of the present invention, a liquid bi-directional pump system is disclosed having a first end and a second end, the liquid bi-directional pump system comprising a gear pump system and first to second three-way reversing valves, wherein:
the first end of the liquid bidirectional pump system is communicated with the left inlet and outlet of the first three-way reversing valve;
the middle inlet and outlet of the first three-way reversing valve, the inlet of the gear pump system and the left inlet and outlet of the second three-way reversing valve are communicated;
the right inlet and outlet of the first three-way reversing valve, the outlet of the gear pump system and the middle inlet and outlet of the second three-way reversing valve are communicated; and
the right inlet and outlet of the second three-way reversing valve is communicated with the second end of the liquid two-way pump system.
According to an exemplary embodiment of the present invention, when liquid is required to flow from the second end to the first end, the gear pump system, the left and right inlets and outlets of the first to second three-way reversing valves are simultaneously opened, and the middle inlets and outlets of the first to second three-way reversing valves are simultaneously closed; when liquid is required to flow from the first end to the second end, the gear pump system, the left inlet and outlet of the first three-way reversing valve, the middle inlet and outlet of the second three-way reversing valve and the right inlet and outlet of the first three-way reversing valve are simultaneously opened, and the right inlet and outlet of the first three-way reversing valve and the left inlet and outlet of the second three-way reversing valve are simultaneously closed.
According to a third aspect of the present invention, there is disclosed a stratospheric airship attitude adjustment device for adjusting a pitch attitude of a stratospheric airship, characterized in that the stratospheric airship attitude adjustment device includes:
the front end liquid storage tank is arranged at the front end of the stratospheric airship;
the rear end liquid storage tank is arranged at the rear end of the stratospheric airship; and
any one of the liquid two-way pump systems is arranged between the front-end liquid storage tank and the rear-end liquid storage tank and below the front-end liquid storage tank and the rear-end liquid storage tank;
wherein the first end of the liquid bi-directional pump system is in communication with the front end reservoir; and
the second end of the liquid bi-directional pump system is in communication with the back end reservoir.
According to an exemplary embodiment of the invention, the front-end tank and/or the rear-end tank has a liquid outlet for releasing the stored liquid outwards for gravitational adjustment of the airship.
According to an exemplary embodiment of the invention, the liquid in the front-end tank and/or the rear-end tank is an antifreeze liquid.
According to an exemplary embodiment of the invention, the front-end tank and/or the rear-end tank is/are flexible bellows.
According to a fourth aspect of the present invention, there is disclosed a stratospheric airship attitude adjustment device for adjusting a pitch attitude of a stratospheric airship, characterized in that the stratospheric airship attitude adjustment device includes:
the front end liquid storage tank is arranged at the front end of the stratospheric airship;
the rear end liquid storage tank is arranged at the rear end of the stratospheric airship; and
the main liquid storage tank is arranged between the front liquid storage tank and the rear liquid storage tank and is positioned below the front liquid storage tank and the rear liquid storage tank; and
the first liquid bidirectional pump system and the second liquid bidirectional pump system of any one of the liquid bidirectional pump systems are adopted, the first liquid bidirectional pump system is arranged between the front-end liquid storage tank and the main liquid storage tank and is positioned below the main liquid storage tank, and the second liquid bidirectional pump system is arranged between the main liquid storage tank and the rear liquid storage tank and is positioned below the main liquid storage tank;
wherein the front end tank communicates with a first end of a first liquid bi-directional pump system;
the second end of the first liquid bidirectional pump system is communicated with the main liquid storage cabin;
the main liquid storage tank is communicated with the first end of the second liquid bidirectional pump system; and
the second end of the second liquid bi-directional pump system is in communication with the back end reservoir.
According to an exemplary embodiment of the invention, the main reservoir has a liquid outlet for releasing the stored liquid outwards for gravitational adjustment of the airship.
According to an exemplary embodiment of the invention, the liquid in the front-end tank, the rear-end tank or the main tank is an antifreeze liquid.
According to an exemplary embodiment of the invention, the front-end tank, the rear-end tank or the main tank is a flexible bladder with a ventilation valve.
According to an example embodiment of the invention, the main reservoir is located directly below the position of the centre of buoyancy of the stratospheric airship.
According to some embodiments of the invention, a feasible method is provided for solving the problem of pitch control of the stratospheric airship in the stratospheric environment, and the function of adjusting the pitch angle posture of the tail rudder on the tail wing can be partially replaced, so that the tail rudder can be removed, and the weight can be reduced.
According to other embodiments of the invention, the centroid and pitch angle postures of the stratospheric airship can be adjusted for multiple times in the stratospheric environment, and the effect of adjusting the angle is obvious.
According to further embodiments of the invention, the gravity adjustment of the airship is achieved by releasing the stored liquid outwards from the main reservoir, and the function of adjusting the buoyancy of the stratospheric airship by the sand-throwing ballast can be taken into account.
It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the invention as claimed.
Drawings
The above and other objects, features and advantages of the present invention will become more apparent by describing in detail exemplary embodiments thereof with reference to the attached drawings.
Fig. 1 shows a schematic diagram of a liquid bi-directional pump system according to an example embodiment of the invention.
Fig. 2 shows a schematic diagram of a liquid bi-directional pump system according to another example embodiment of the invention.
Fig. 3 shows a schematic view of a stratospheric airship attitude adjustment device according to an example embodiment of the invention, employing the liquid bi-directional pump system shown in fig. 1 or 2.
Fig. 4 shows a schematic view of a stratospheric airship attitude adjustment device according to another example embodiment of the invention, employing the liquid bi-directional pump system shown in fig. 1 or 2.
Detailed Description
Example embodiments will now be described more fully with reference to the accompanying drawings. However, the exemplary embodiments can be embodied in many forms and should not be construed as limited to the embodiments set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the concept of the example embodiments to those skilled in the art. The same reference numerals in the drawings denote the same or similar parts, and thus a repetitive description thereof will be omitted.
Furthermore, the described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments. In the following description, numerous specific details are provided to give a thorough understanding of embodiments of the invention. One skilled in the relevant art will recognize, however, that the invention may be practiced without one or more of the specific details, or with other methods, components, devices, steps, etc. In other instances, well-known methods, devices, implementations, or operations are not shown or described in detail to avoid obscuring aspects of the invention.
The block diagrams depicted in the figures are merely functional entities and do not necessarily correspond to physically separate entities. That is, the functional entities may be implemented in software, or in one or more hardware modules or integrated circuits, or in different networks and/or processor devices and/or microcontroller devices.
The flow diagrams depicted in the figures are exemplary only, and do not necessarily include all of the elements and operations/steps, nor must they be performed in the order described. For example, some operations/steps may be decomposed, and some operations/steps may be combined or partially combined, so that the order of actual execution may be changed according to actual situations.
It will be understood that, although the terms first, second, third, etc. may be used herein to describe various components, these components should not be limited by these terms. These terms are used to distinguish one element from another element. Accordingly, a first component discussed below could be termed a second component without departing from the teachings of the present inventive concept. As used herein, the term "and/or" includes any one of the associated listed items and all combinations of one or more.
Those skilled in the art will appreciate that the drawings are schematic representations of example embodiments and that the modules or flows in the drawings are not necessarily required to practice the invention and therefore should not be taken to limit the scope of the invention.
The invention aims to disclose a liquid bi-directional pump system and a stratospheric airship posture adjusting device adopting the same. The liquid bi-directional pump system has a first end and a second end, including a gear pump system and first through fourth solenoid valves, wherein: the first end of the liquid bi-directional pump system, the first end of the first solenoid valve and the first end of the fourth solenoid valve are communicated; the second end of the first electromagnetic valve, the inlet of the gear pump system and the first end of the third electromagnetic valve are communicated; the second end of the fourth electromagnetic valve, the outlet of the gear pump system and the first end of the second electromagnetic valve are communicated; and a second end of the third solenoid valve, a second end of the second solenoid valve, and a second end of the liquid bi-directional pump system. The stratospheric airship attitude adjusting device adopting the liquid bi-directional pump system changes the centroid and the pitching attitude of the stratospheric airship by changing the mass of liquid in the end liquid storage cabin. The stratospheric airship attitude adjusting device provides a feasible method for solving the problem of pitching control of the stratospheric airship in the stratospheric environment, and can partially replace the function of adjusting the pitch angle attitude of the tail rudder on the tail wing, so that the tail rudder is removed, and the weight is reduced. Meanwhile, the mass center and pitch angle postures of the stratospheric airship can be adjusted for multiple times in the stratospheric environment, and the effect of adjusting the angle is obvious. In addition, the stored liquid is released outwards through the main liquid storage cabin so as to realize gravity adjustment of the airship, and the function of adjusting buoyancy of the stratospheric airship through sand throwing ballast can be taken into consideration.
The liquid bi-directional pump system and the stratospheric airship attitude adjustment device using the same according to the invention will be specifically described with reference to fig. 1-4, where fig. 1 shows a schematic view of a liquid bi-directional pump system according to an example embodiment of the invention; FIG. 2 shows a schematic diagram of a liquid bi-directional pump system according to another example embodiment of the invention; FIG. 3 illustrates a schematic diagram of a stratospheric airship attitude adjustment device employing the liquid bi-directional pump system illustrated in FIG. 1 or 2 according to one example embodiment of the invention; fig. 4 shows a schematic view of a stratospheric airship attitude adjustment device according to another example embodiment of the invention, employing the liquid bi-directional pump system shown in fig. 1 or 2.
A stratospheric airship attitude adjustment device according to an example embodiment of the invention will be described in detail with reference to fig. 1, in which fig. 1 shows a schematic view of a liquid bi-directional pump system according to an example embodiment of the invention.
As shown in fig. 1, the liquid bi-directional pump system has a first end a and a second end B, comprising a gear pump system 10 and first through fourth solenoid valves 11-14, wherein: the first end A of the liquid bi-directional pump system, the first end of the first solenoid valve 11 and the first end of the fourth solenoid valve 14 are in communication; the second end of the first solenoid valve 11, the inlet of the gear pump system 10 and the first end of the third solenoid valve 13 are in communication; a second end of the fourth solenoid valve 14, an outlet of the gear pump system 10, and a first end of the second solenoid valve 12 are in communication; and a second end of the third solenoid valve 13, a second end of the second solenoid valve 12 and a second end B of the liquid bi-directional pump system.
According to an exemplary embodiment of the present invention, the communication is via an infusion line with temperature control.
According to an exemplary embodiment of the invention, wherein the gear pump system, the third solenoid valve and the fourth solenoid valve are simultaneously opened and the first solenoid valve and the second solenoid valve are simultaneously closed when liquid is required to flow from the second end to the first end; when liquid is required to flow from the first end to the second end, the gear pump system, the first electromagnetic valve and the second electromagnetic valve are simultaneously opened, and the third electromagnetic valve and the fourth electromagnetic valve are simultaneously closed. That is, the liquid bi-directional pump system of the present invention can achieve either liquid flow from the second end to the first end or liquid flow from the first end to the second end as desired.
Fig. 2 shows a schematic diagram of a liquid bi-directional pump system according to another example embodiment of the invention.
As shown in fig. 2, the liquid bi-directional pump system has a first end a and a second end B, comprising a gear pump system 10 and first to second three-way reversing valves 15-16, wherein: the first end of the liquid two-way pump system is communicated with the left inlet and outlet of the first three-way reversing valve 15; the middle inlet and outlet of the first three-way reversing valve 15, the inlet of the gear pump system and the left inlet and outlet of the second three-way reversing valve 16 are communicated; the right inlet and outlet of the first three-way reversing valve 15, the outlet of the gear pump system and the middle inlet and outlet of the second three-way reversing valve 16 are communicated; and the right inlet and outlet of the second three-way reversing valve 16 communicates with the second end of the liquid bi-directional pump system.
According to an exemplary embodiment of the present invention, wherein when liquid is required to flow from the second end to the first end, the left and right inlets and outlets of the gear pump system, the first to second three-way directional valves 15 to 16 are simultaneously opened, and the middle inlets and outlets of the first to second three-way directional valves 15 to 16 are simultaneously closed; when the liquid is required to flow from the first end to the second end, the gear pump system, the left inlet and outlet of the first three-way reversing valve 15, the middle inlet and outlet of the second three-way reversing valve 16, and the middle inlet and outlet and the right inlet and outlet of the second three-way reversing valve 16 are simultaneously opened, and the right inlet and outlet of the first three-way reversing valve 15 and the left inlet and outlet of the second three-way reversing valve 16 are simultaneously closed.
A schematic diagram of a stratospheric airship attitude adjustment device according to an example embodiment of the invention, using the liquid bi-directional pump system shown in fig. 1 or 2, is shown below with reference to fig. 3.
As shown in fig. 3, the stratospheric airship attitude adjusting device according to an example embodiment includes: the front end liquid storage cabin 2 is arranged at the front end of the stratospheric airship; the rear end liquid storage cabin 6 is arranged at the rear end of the stratospheric airship; and a liquid bi-directional pump system 4 as in any of the preceding claims, disposed between and below the front and rear tanks; wherein the first end of the liquid bi-directional pump system is in communication with the front end reservoir; and a second end of the liquid bi-directional pump system is in communication with the back-end reservoir. Wherein the stratospheric airship comprises an outer capsule 5. That is, the attitude adjusting device of the stratospheric airship of the invention causes liquid to flow from the front end liquid storage tank 2 to the rear end liquid storage tank 6 or from the rear end liquid storage tank 6 to the front end liquid storage tank 2 through the liquid bi-directional pump system, thereby changing the mass center and the pitching attitude of the stratospheric airship by changing the mass of the liquid in the end liquid storage tanks
According to an example embodiment of the invention, the stratospheric airship is fusiform.
According to an exemplary embodiment of the invention, the front-end liquid storage tank and/or the rear-end liquid storage tank are/is provided with liquid outlets 1 and 7 for outwards releasing the stored liquid so as to realize gravity adjustment of the airship, thereby realizing the function of adjusting the buoyancy of the stratospheric airship by throwing sand ballast and realizing the optimal combination of various adjustment modes.
According to an exemplary embodiment of the invention, the liquid in the front-end tank and/or the rear-end tank is an antifreeze liquid.
According to an exemplary embodiment of the invention, the antifreeze is adapted to a temperature in the range from-80 ℃ to +80 ℃, i.e. in the low temperature and low pressure environment of the stratosphere, the antifreeze is to be ensured not to freeze at-80 ℃ and not to vaporize at +80 ℃ (the boiling point of the liquid is significantly reduced under low pressure conditions).
According to an exemplary embodiment of the invention, the temperature adaptation of the antifreeze is in the range-70 ℃ to +75 ℃.
According to an exemplary embodiment of the invention, the main reservoir and the end reservoirs are flexible bellows with air-permeable valves.
According to an exemplary embodiment of the invention, wherein the communication takes place through the infusion line 3. The infusion pipeline 3 can be made of a light rust-resistant, high-pressure-resistant and high-low temperature-alternating-resistant pipe with certain rigidity in the radial direction.
The mechanism of adjustment of the centroid and pitch attitude angle of the stratospheric airship of the present example embodiment is as follows:
the front end liquid storage cabin 2 and the rear end liquid storage cabin 6 are both in a sealing state.
When the front end of the stratospheric airship needs to be adjusted and the pitching attitude angle of the stratospheric airship is low, the liquid bi-directional pump system 4 pumps and conveys the liquid in the rear-end liquid storage cabin 6 to the front-end liquid storage cabin 2 through the liquid conveying pipeline 3.
When the front end of the stratospheric airship needs to be lifted by adjusting the pitching attitude angle of the stratospheric airship, the liquid bi-directional pump system 4 pumps out and conveys the liquid in the front-end liquid storage tank 2 to the rear-end liquid storage tank 6 through the liquid delivery pipeline 3.
A stratospheric airship attitude adjustment device according to another example embodiment of the invention will be described in detail with reference to fig. 4, where fig. 4 shows a schematic view of a stratospheric airship attitude adjustment device according to another example embodiment of the invention, using the liquid bi-directional pump system shown in fig. 1 or 2.
As shown in fig. 4, the stratospheric airship attitude adjusting device according to an example embodiment includes: the front end liquid storage cabin 2 is arranged at the front end of the stratospheric airship; the rear end liquid storage cabin 6 is arranged at the rear end of the stratospheric airship; the main liquid storage tank 9 is arranged between the front liquid storage tank and the rear liquid storage tank and is positioned below the front liquid storage tank and the rear liquid storage tank; and first to second liquid bi-directional pump systems 4 and 4 'employing a liquid bi-directional pump system as described in any of the preceding claims, the first liquid bi-directional pump system 4 being disposed between the front tank and the main tank and below the main tank, the second liquid bi-directional pump system 4' being disposed between the main tank and the rear tank and below the main tank; wherein the front end tank communicates with a first end of a first liquid bi-directional pump system; the second end of the first liquid bidirectional pump system is communicated with the main liquid storage cabin; the main liquid storage tank is communicated with the first end of the second liquid bidirectional pump system; and a second end of the second liquid bi-directional pump system is in communication with the back-end reservoir. Wherein the stratospheric airship comprises an outer capsule 5. Also, the stratospheric airship attitude adjustment device of the present example embodiment changes the centroid and pitch attitude of the stratospheric airship by changing the mass of the liquid in the end reservoir.
According to an example embodiment of the invention, the stratospheric airship is fusiform.
According to an exemplary embodiment of the invention, the main reservoir has a liquid outlet 8 for releasing the stored liquid outwards to realize gravity adjustment of the airship, so that the function of adjusting the buoyancy of the stratospheric airship by the sand throwing ballast can be taken into account, and the optimal combination of various adjustment modes can be realized.
According to an exemplary embodiment of the invention, the liquid in the front-end tank and/or the rear-end tank and in the main tank is antifreeze.
According to an exemplary embodiment of the invention, the antifreeze is adapted to a temperature in the range from-80 ℃ to +80 ℃, i.e. in the low temperature and low pressure environment of the stratosphere, the antifreeze is to be ensured not to freeze at-80 ℃ and not to vaporize at +80 ℃ (the boiling point of the liquid is significantly reduced under low pressure conditions).
According to an exemplary embodiment of the invention, the temperature adaptation of the antifreeze is in the range-70 ℃ to +75 ℃.
According to an exemplary embodiment of the invention, the main reservoir and the end reservoirs are flexible bellows with air-permeable valves.
According to an exemplary embodiment of the invention, the communication takes place through a temperature-controlled infusion line 3. The infusion pipeline 3 can be made of a light rust-resistant, high-pressure-resistant and high-low temperature-alternating-resistant pipe with certain rigidity in the radial direction.
According to an example embodiment of the invention, the main reservoir is located directly below the position of the centre of buoyancy of the stratospheric airship.
The mechanism of adjustment of the centroid and pitch attitude angle of the stratospheric airship of the present example embodiment is as follows:
the front end liquid storage cabin 2, the main liquid storage cabin 9 and the rear end liquid storage cabin 6 are all in a sealed state.
The two liquid bi-directional pump systems 4 and 4' are turned on when the forward end of the stratospheric airship needs to be adjusted to have a low pitch attitude angle. The liquid in the rear end liquid storage cabin 6 and the main liquid storage cabin 9 is pumped out of the front end liquid storage cabin 2 through the liquid delivery pipeline 3.
The two liquid bi-directional pump systems 4 and 4' are turned on when the front end of the stratospheric airship needs to be lifted by adjusting the pitch attitude angle of the stratospheric airship. The liquid in the front-end liquid storage tank 2 and the liquid in the middle liquid storage tank 9 are pumped out through the liquid delivery pipeline 3 and are delivered to the rear-end liquid storage tank 6.
As will be readily appreciated by those skilled in the art from the above detailed description, the stratospheric airship attitude adjusting device according to the embodiment of the invention has the following advantages.
According to some embodiments of the invention, a feasible method is provided for solving the problem of pitch control of the stratospheric airship in the stratospheric environment, and the function of adjusting the pitch angle posture of the tail rudder on the tail wing can be partially replaced, so that the tail rudder can be removed, and the weight can be reduced.
According to other embodiments of the invention, the centroid and pitch angle postures of the stratospheric airship can be adjusted for multiple times in the stratospheric environment, and the effect of adjusting the angle is obvious.
According to further embodiments of the invention, the gravity adjustment of the airship is achieved by releasing the stored liquid outwards from the main reservoir, and the function of adjusting the buoyancy of the stratospheric airship by the sand-throwing ballast can be taken into account.
Other embodiments of the invention will be apparent to those skilled in the art from consideration of the specification and practice of the invention disclosed herein. This application is intended to cover any variations, uses, or adaptations of the invention following, in general, the principles of the invention and including such departures from the present disclosure as come within known or customary practice within the art to which the invention pertains. It is intended that the specification and examples be considered as exemplary only, with a true scope and spirit of the invention being indicated by the following claims.
It is to be understood that the invention is not limited to the precise arrangements and instrumentalities shown in the drawings, which have been described above, and that various modifications and changes may be effected without departing from the scope thereof. The scope of the invention is limited only by the appended claims.
Claims (11)
1. A liquid bi-directional pump system having a first end and a second end, the liquid bi-directional pump system comprising a gear pump system and first through fourth solenoid valves, wherein:
the first end of the liquid bi-directional pump system, the first end of the first solenoid valve and the first end of the fourth solenoid valve are communicated;
the second end of the first electromagnetic valve, the inlet of the gear pump system and the first end of the third electromagnetic valve are communicated;
the second end of the fourth electromagnetic valve, the outlet of the gear pump system and the first end of the second electromagnetic valve are communicated; and
the second end of the third electromagnetic valve, the second end of the second electromagnetic valve and the second end of the liquid bidirectional pump system are communicated;
when the liquid is required to flow from the second end to the first end, the gear pump system, the third electromagnetic valve and the fourth electromagnetic valve are simultaneously opened, and the first electromagnetic valve and the second electromagnetic valve are simultaneously closed; when liquid is required to flow from the first end to the second end, the gear pump system, the first electromagnetic valve and the second electromagnetic valve are simultaneously opened, and the third electromagnetic valve and the fourth electromagnetic valve are simultaneously closed.
2. The bi-directional liquid pump system of claim 1 wherein the communication is through a temperature controlled infusion line.
3. A stratospheric airship attitude adjustment device for adjusting a pitch attitude of a stratospheric airship, characterized in that the stratospheric airship attitude adjustment device comprises:
the front end liquid storage tank is arranged at the front end of the stratospheric airship;
the rear end liquid storage tank is arranged at the rear end of the stratospheric airship; and
the liquid bi-directional pump system of any one of claims 1 or 2, disposed between and below the front and rear tanks;
wherein the first end of the liquid bi-directional pump system is in communication with the front end reservoir; and
the second end of the liquid bi-directional pump system is in communication with the back end reservoir.
4. A stratospheric airship attitude adjustment device according to claim 3, wherein the front end tank and/or the rear end tank has a liquid outlet for releasing the stored liquid outwards to effect gravitational adjustment of the airship.
5. A stratospheric airship attitude adjustment device according to claim 3, wherein the liquid in the front-end liquid storage tank and/or the rear-end liquid storage tank is antifreeze.
6. A stratospheric airship attitude adjustment device according to claim 3, wherein the front end tank and/or the rear end tank is a flexible bladder with a ventilation valve.
7. A stratospheric airship attitude adjustment device for adjusting a pitch attitude of a stratospheric airship, characterized in that the stratospheric airship attitude adjustment device comprises:
the front end liquid storage tank is arranged at the front end of the stratospheric airship;
the rear end liquid storage tank is arranged at the rear end of the stratospheric airship; and
the main liquid storage tank is arranged between the front liquid storage tank and the rear liquid storage tank and is positioned below the front liquid storage tank and the rear liquid storage tank; and
a first to a second liquid bi-directional pump system employing the liquid bi-directional pump system according to any one of claims 1 or 2, the first liquid bi-directional pump system being disposed between the front-end tank and the main tank and below the main tank, the second liquid bi-directional pump system being disposed between the main tank and the rear tank and below the main tank;
wherein the front end tank communicates with a first end of a first liquid bi-directional pump system;
the second end of the first liquid bidirectional pump system is communicated with the main liquid storage cabin;
the main liquid storage tank is communicated with the first end of the second liquid bidirectional pump system; and
the second end of the second liquid bi-directional pump system is in communication with the back end reservoir.
8. The stratospheric airship attitude adjustment device of claim 7, wherein the main reservoir has a liquid outlet for releasing the stored liquid outwardly to effect gravitational adjustment of the airship.
9. The stratospheric airship attitude adjustment device according to claim 7, wherein the liquid in the front-end tank, the rear-end tank or the main tank is an antifreeze solution.
10. The stratospheric airship attitude adjustment device according to claim 7, wherein the front-end tank, the rear-end tank, or the main tank is a flexible bladder with a ventilation valve.
11. The stratospheric airship attitude adjustment device of claim 7, wherein the main reservoir is located directly below the position of the center of buoyancy of the stratospheric airship.
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| CN201811351590.7A CN109398672B (en) | 2018-11-14 | 2018-11-14 | Liquid bidirectional pump system and stratospheric airship attitude adjusting device adopting same |
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| CN201811351590.7A CN109398672B (en) | 2018-11-14 | 2018-11-14 | Liquid bidirectional pump system and stratospheric airship attitude adjusting device adopting same |
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| CN109398672B true CN109398672B (en) | 2024-03-15 |
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| CN111516850B (en) * | 2020-04-02 | 2023-05-09 | 湖南航天远望科技有限公司 | Control method for flight attitude and buoyancy of airship |
| CN112524020B (en) * | 2020-12-28 | 2024-03-19 | 合肥皖液液压元件有限公司 | High-pressure gear pump with large discharge capacity |
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