CN114104251A - Reciprocating type stratospheric airship capable of being repeatedly used during overlong navigation - Google Patents
Reciprocating type stratospheric airship capable of being repeatedly used during overlong navigation Download PDFInfo
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- CN114104251A CN114104251A CN202111579333.0A CN202111579333A CN114104251A CN 114104251 A CN114104251 A CN 114104251A CN 202111579333 A CN202111579333 A CN 202111579333A CN 114104251 A CN114104251 A CN 114104251A
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/58—Arrangements or construction of gas-bags; Filling arrangements
Abstract
The invention discloses a reciprocating type super-long reusable stratospheric airship during navigation, which comprises: the air bag system comprises a main bag body, an air bag and an empennage, and buoyancy gas is filled in the main bag body; the air bag is fixed inside the main bag body and is used for filling air; the pod group is fixed at the bottom of the outer side of the main bag body; the energy system comprises a solar cell array, an energy storage cell and an energy manager, wherein the solar cell array is fixed at the top of the outer side of the main bag body, and the energy storage cell is fixed in the pod group; the power system comprises a propeller power device and a steering device for controlling the propeller to change the torque, the pressure regulating system comprises a main bag body air release valve, an air bag air suction and exhaust device and a floating gas pressure regulating device, the main bag body air release valve is fixed on the main bag body, and the air bag air suction and exhaust device is fixed on the outer side of the main bag body and is communicated with the air bag through a pipeline to suck and exhaust air; the flight control system controls the propeller power device and the steering device through signals.
Description
Technical Field
The invention relates to the technical field of near space aircrafts, in particular to a reciprocating type stratospheric airship capable of being repeatedly used during overlong navigation.
Background
The near space is an aerospace combination area of the flying height of the aircraft and the orbit height of the spacecraft, is an airspace of 18-100 kilometers, mainly takes east-west wind as the main part, basically has no weather phenomenon, does not belong to the field of national air-receiving management in the world, has unique environmental advantages and huge potential military and civil application efficiency, is the field of development and space utilization of various countries, and has important strategic and industrial values. The stratospheric airship is a floating aircraft which realizes 'lifting, parking and returning' by static buoyancy under the natural environmental conditions of sufficient solar energy, stable environment and the like near the 20km height of a near space, and has irreplaceable advantages and effects in the aspects of high-resolution ground observation, regional reconnaissance and monitoring, target early warning detection, battlefield environment detection, electronic reconnaissance and countermeasure, high-altitude communication relay capacity and the like by the characteristics of large load, fixed point/region parking and high use efficiency-cost ratio.
At present, the research and development level of stratospheric airship technologies at home and abroad is still in the same fleet, the overall technical system always faces the difficult problems of overpressure forming safety of a buoyancy bag body and stable buoyancy caused by diurnal super-thermal circulation in the long-term sky-parking process, and the requirements of energy balance and dynamic resistance balance are met. The prior art approach mainly adopts: (a) the buoyancy bag body has the advantages that the safe pressure bearing capacity of the buoyancy bag body is utilized to firmly resist excessive heat and overpressure in the daytime and keep forming at night to maintain certain basic pressure difference, but the strength density ratio and the processing technology level of the bag body material are limited, the strength exertion rate and the leakage rate of the large-size bag body after processing and forming are greatly lower than the performance of the material, so that the buoyancy bag body of the airship platform is limited in size, insufficient in the process of parking and navigating and in the load capacity, and the requirement of forming lifting capacity is difficult to be considered; (b) the semi-rigid skeleton system is used for realizing basic forming and bearing force, so that the buoyancy capsule body is maintained at a low-pressure level, the capacity of parking in the air is improved, but the larger skeleton weight enables the closed loop of the self capacity of the platform to greatly increase the size of the buoyancy capsule body, the ground assembly integration and the flying recovery guarantee are high in difficulty, high in cost and low in bearing force, and the feasibility of engineering implementation is difficult to take into account.
Therefore, how to provide a long-term sky-parking stratospheric airship which can be repeatedly used during super-long navigation is a problem to be solved by those skilled in the art.
Disclosure of Invention
In view of the above, the present invention provides a reciprocating type stratospheric airship capable of being repeatedly used during an ultra-long voyage, which can sail in the near space day and night for a long time, and controls the overpressure balance of the main bag body by changing the amount of the buoyancy gas and the gas in the gas storage device.
In order to achieve the purpose, the invention adopts the following technical scheme: a reciprocating overlength, reusable stratospheric airship, comprising:
the airbag system comprises a main airbag body, an air bag and an empennage, wherein the main airbag body is of a streamline solid structure, the inner side wall of the main airbag body is fixedly connected with a supporting framework, and buoyancy gas is filled in the main airbag body; the air bag is fixed inside the main bag body, and air is filled in the air bag; the tail wing is arranged on the outer side of the tail end of the main bag body;
the pod group is fixed at the outer bottom of the main bag body; electronic equipment and energy equipment are arranged in the pod group;
the energy system comprises a solar cell array, an energy storage cell and an energy manager, wherein the solar cell array is fixed at the top of the outer side of the main bag body, and the energy storage cell is fixed in the pod group; the energy manager distributes and controls the working states of the energy equipment and the energy storage battery;
the power system comprises a propeller power device and a steering device for controlling the variable torque of the propeller, and the propeller power device and the steering device are both positioned at the tail end of the main bag body;
the pressure regulating system comprises a main bag body air release valve, an air bag air suction and exhaust device and a floating gas pressure regulating device, wherein the main bag body air release valve is fixed on the main bag body and used for releasing floating gas in the main bag body, and the air bag air suction and exhaust device is fixed on the outer side of the main bag body and communicated with the air bag through a pipeline to suck and exhaust air; the buoyancy gas pressure adjusting device comprises a gas storage device and a gas compressor, the gas storage device is fixed inside the main bag body and is provided with a gas inlet and a gas outlet, the gas inlet is connected with the gas compressor to press the buoyancy gas in the main bag body into the gas storage device, and the gas outlet is connected with a dual-redundancy gas release valve to release the buoyancy gas in the gas storage device so as to control the overpressure balance of the main bag body;
and the flight control system controls the propeller power device and the steering device through signals.
The invention has the beneficial effects that: in the invention, an air bag is arranged in the main bag body, the main bag body is filled with buoyancy gas to generate upward lifting force of the main bag body, the air bag is filled with air, under the condition of certain floating gas, the lifting of the main bag body is adjusted through the air quantity filled with air in the air bag, the air storage device is arranged in the main bag body, the buoyancy gas expands due to direct sunlight in the daytime in the adjacent space, the internal pressure of the main bag body is increased, the risk of bursting exists, at the moment, partial buoyancy gas is pressed into the air storage device through the air compressor, the overpressure balance of the main bag body in the daytime is ensured, at night, the temperature is reduced, the buoyancy gas is contracted, the pressure in the main bag body is reduced, at the moment, the gas storage device releases the buoyancy gas into the main bag body through the dual-redundancy air release valve, the overpressure balance and stable navigation of the main bag body at night are ensured, and the main bag body can navigate in the adjacent space for a long time.
Preferably, the length of the main bag body is 90-130 m, the slenderness ratio of the main bag body is 3-4, the main bag body is formed by laminating high-strength fabric and composite materials, the outer surface of the main bag body is provided with a thermal control coating, and the air bag is formed by machining a light high-elasticity film or a film bearing fabric material.
Preferably, the pod group comprises an equipment cabin, an energy cabin, a counterweight cabin and a load cabin, wherein the equipment cabin, the energy cabin, the counterweight cabin and the load cabin are all in a low-resistance streamline configuration or a fairing drag reduction configuration and are respectively fixed at the bottom of the outer side of the main capsule body, and phase change material layers for controlling the temperature in the cabin are arranged on the inner side walls of the equipment cabin and the energy cabin.
Preferably, the flight control system comprises a dual-redundancy high-performance computer, a combined inertial navigation device and a signal bus, the dual-redundancy high-performance computer is arranged in an equipment cabin, the combined inertial navigation device is arranged in the equipment cabin or on the outer surface of a main bag body, the signal bus is respectively connected with the combined inertial navigation device and the dual-redundancy high-performance computer, and the dual-redundancy high-performance computer realizes remote measurement and remote control information management of the propeller power device and the steering device through embedded software.
Preferably, the air bag suction and exhaust device comprises an air release valve and an air blower, the air release valve is fixedly communicated with a bypass of a blast port of the air blower, a flange interface is reserved on the main bag body, the air bag is connected with the flange interface through a pipeline to achieve communication with the outside, the air blower and the air release valve are fixed on the outer side of the flange interface, the air bag releases air in the air bag through the air release valve, and the air blower blows air into the air bag to adjust the lifting of the main bag body.
Preferably, the supporting framework comprises a hoop framework, a longitudinal framework and a tension cable, the hoop framework and the longitudinal framework are fixedly connected to the inner side wall of the main bag body respectively, the tension cable comprises a plurality of tension cables, and the tension cables are respectively crossed and tied on the hoop framework.
Preferably, the bottom of the main bag body is fixedly connected with a buffer device, the buffer device comprises a buffer airbag and a gas generator, and the gas generator is rapidly inflated to expand the buffer airbag.
Preferably, the system also comprises a measurement and control system, wherein the measurement and control system comprises a line-of-sight measurement and control terminal and a satellite measurement and control terminal, the line-of-sight measurement and control terminal and the satellite measurement and control terminal are arranged in the equipment cabin or on the surface of the main capsule body, and the line-of-sight measurement and control terminal and the satellite measurement and control terminal provide a remote measurement and control communication link for mutual backup of the line-of-sight distance of the boat and the over-the-horizon distance.
Preferably, the lift gas is helium, hydrogen or a mixed gas of hydrogen and an inert gas, wherein the inert gas is an inert gas with a density less than that of air.
Preferably, the gas storage device is spherical, is made of high-strength flexible composite materials, has a diameter of 10-30 m, and is hung at the top of the inner side of the main bag body through a restraint rope and a pull-mixing device.
Drawings
FIG. 1 is a schematic view of the overall structure of a reciprocating type stratospheric airship which can be repeatedly used during ultra-long voyage;
FIG. 2 is a schematic view of the retraction of the cushion of a reciprocating type super-long endurance stratospheric airship of the present invention;
FIG. 3 is a schematic view of the ground state of a reciprocating type super-long airship of the stratosphere reusable in navigation;
FIG. 4 is a schematic view of a reciprocating type stratospheric airship repeatedly usable during ultra-long voyage in an ascending state according to the present invention;
FIG. 5 is a schematic view of a reciprocating type very long airship of the stratosphere reusable in flight in the near space;
fig. 6 is a schematic diagram of the circulation of buoyant gas in a reciprocating type super-long airship of the stratosphere that can be reused during navigation.
The device comprises a main bag body 1, an air bag 2, a tail wing 3, a support framework 4, a solar cell array 5, a propeller power device 6, a steering device 7, a main bag body deflation valve 8, an air bag suction and exhaust device 9, an air bag deflation valve 901, an air blower 902, a buoyancy gas pressure adjusting device 10, an air storage device 101, an air compressor 102, a dual-redundancy deflation valve 103, an equipment cabin 11, an energy cabin 12, a counterweight cabin 13, a load cabin 14, a buffer device 15 and buoyancy gas 16.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the 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.
Referring to fig. 1 to 5 of the drawings, a reciprocating type super-long stratospheric airship reusable during navigation according to an embodiment of the invention is characterized by comprising:
the airbag system comprises a main airbag body 1, an air bag 2 and an empennage 3, wherein the main airbag body 1 is of a streamline solid structure, the inner side wall of the main airbag body 1 is fixedly connected with a supporting framework 4, the supporting framework 4 has necessary supporting and bearing capacity, the integral bearing performance of the main airbag body is improved, and buoyancy gas 16 is filled in the main airbag body 1; the air bag 2 is fixed inside the main bag body 1 and is used for filling air; the empennage is arranged on the outer side of the tail end of the main bag body 1; the buoyancy lifting gas 16 is a lifting energy source, the total amount of the buoyancy lifting gas is certain, but partial buoyancy lifting gas is pressed into the gas storage device by the gas compressor according to the pressure of the main bag body, and the overpressure balance of the main bag body is kept. In addition, the lifting of the main bag body is adjusted according to the amount of the air sucked into the air bag.
The pod group is fixed at the bottom of the outer side of the main bag body; electronic equipment and energy equipment are arranged in the pod group; the electronic equipment is used for necessary detection and control, the energy equipment is used for supplying energy and power to ensure necessary energy supply of the airship, the energy equipment can adopt a small nuclear reactor or a laser energy transmission mode, and the laser energy transmission is realized by utilizing a laser emitting device and a laser energy receiving device.
The energy system comprises a solar cell array 5, an energy storage cell and an energy manager, wherein the solar cell array 5 is fixed at the top of the outer side of the main bag body 1 and used for receiving solar energy in the daytime, and the energy storage cell is fixed in the pod group; energy storage, wherein the energy manager distributes and controls the working states of the energy equipment and the energy storage battery; distributing energy supply to provide necessary energy supply for the electronic equipment or electric equipment equipped on the airship,
the power system comprises a propeller power device 6 and a steering device 7 for controlling the variable torque of the propeller, wherein the propeller power device 6 and the steering device are both positioned at the tail end of the main bag body; the thrust of the airship navigation is provided, and the efficient full-scale power output and the adjustment of the thrust and the lift direction in the flight section can be realized.
The pressure regulating system comprises a main bag body air release valve 8, an air bag air suction and exhaust device 9 and a floating gas pressure regulating device 10, wherein the main bag body air release valve 8 is fixed on the main bag body 1 and used for releasing floating gas in the main bag body, and the air bag air suction and exhaust device 9 is fixed on the outer side of the main bag body 1 and communicated with the air bag 2 through a pipeline to suck and exhaust air; the air bag and the main bag body are independent units, the buoyancy gas pressure adjusting device 10 comprises a gas storage device 101 and a gas compressor 102, the gas storage device 101 is fixed inside the main bag body 1, the gas storage device 101 is provided with a gas inlet and a gas outlet, the gas inlet is connected with the gas compressor 102 to press the buoyancy gas in the main bag body 1 into the gas storage device 101, and the gas outlet is connected with a dual-redundancy gas release valve 103 to release the buoyancy gas in the gas storage device to control the overpressure balance of the main bag body; partial buoyancy gas can be pressed into the gas storage device according to the pressure requirement in the main bag body in the day and at night, or the buoyancy gas in the gas storage device is released by the dual-redundancy gas release valve 103 according to the pressure condition of the main bag body, so that the overpressure balance of the main bag body in the whole day or night is realized.
And the flight control system controls the propeller power device and the steering device through signals. The remote control navigation of the airship is realized.
In other embodiments, the length of the main bag body 1 is 130m, the slenderness ratio of the main bag body 1 is 4, the main bag body 1 is formed by laminating high-strength fabric and composite material, the specific material can be high-strength polyester and polyethylene composite material, the outer surface of the main bag body is provided with a thermal control coating and an anti-icing coating, and the air bag 1 is formed by processing light high-elasticity film or film bearing fabric material. Silicone rubber may be selected.
In other embodiments, the pod group comprises an equipment cabin 11, an energy cabin 12, a counterweight cabin 13 and a load cabin 14, wherein the equipment cabin 11, the energy cabin 12, the counterweight cabin 13 and the load cabin 14 are all in low-resistance streamline configuration or fairing drag reduction configuration to reduce navigation resistance, the equipment cabin 11, the energy cabin 12, the counterweight cabin 13 and the load cabin 14 are respectively fixed at the bottom of the outer side of the main capsule body, and phase change material layers for controlling the temperature in the cabin are arranged on the inner side walls of the equipment cabin and the energy cabin. The heat energy in the daytime is stored in the phase change heat storage material, the temperature in the equipment cabin is maintained after the heat energy is released at night, and the reliable working environment of the electronic equipment in the equipment cabin at minus 40 ℃ to plus 55 ℃ is maintained to overcome the influence of the low-temperature and low-pressure environment of the stratosphere.
In other embodiments, the flight control system comprises a dual-redundancy high-performance computer, a combined inertial navigation device and a signal bus, wherein the dual-redundancy high-performance computer is arranged in the equipment cabin, the combined inertial navigation device is arranged in the equipment cabin or on the outer surface of the main bag body, the signal bus is respectively connected with the combined inertial navigation device and the dual-redundancy high-performance computer, and the dual-redundancy high-performance computer realizes remote measurement and remote control information management of the propeller power device and the steering device through embedded software. The combined inertial navigation device can be a GPS navigation device or a Beidou navigation device, and the navigation device is used for controlling a route.
Specifically, the air bag suction and exhaust device 9 includes a deflation valve 901 and a blower 902, the deflation valve 901 is fixedly communicated on a side path of a blowing port of the blower 902, the deflation of the air bag is not affected, a flange interface is reserved on the main bag body 1, the air bag 2 is connected with the flange interface through a pipeline to realize the communication with the outside, the blower and the deflation valve are fixed on the outside of the flange interface, the air bag releases the air in the air bag through the deflation valve, and the blower blows the air into the air bag to regulate the lifting of the main bag body. The weight restraint is realized through the amount of air filled in the main bag body, and the control effect of the whole ascending or descending of the airship is completed.
In other embodiments, the supporting frame 4 includes a circumferential frame, a longitudinal frame and a tension cable, the circumferential frame and the longitudinal frame are respectively and fixedly connected to the inner side wall of the main bag body 1 to provide auxiliary supporting load of the main bag body, the tension cable includes a plurality of tension cables, and the tension cables are respectively and alternately tied on the circumferential frame to maintain the overall stability of the supporting frame. The tension of the tension cable is adjusted to be connected with the circumferential framework and the longitudinal framework to form a stable bearing structure, so that the stress distribution and the dimensional pressure level of the main capsule can be effectively reduced, and the installation reliability and the stress transmission uniformity of each cabin and the power system are improved. The circumferential framework adopts a high-strength composite material inflatable structure or a carbon fiber truss structure, the outer contour of the circumferential framework is circular or polygonal, and the number of the circumferential framework is 3-8; the longitudinal skeleton adopts a high-strength carbon fiber cylindrical rod or truss structure, and the number of the longitudinal skeleton is 3-6; the tension cable is a high-strength nylon rope or a steel cable. Multidirectional diagonal distribution; the high-efficiency forming and descending system is a key system for realizing the low-pressure maintenance of good pneumatic appearance rigidity of the airship platform and the high-efficiency forming and descending under a certain negative pressure.
In other embodiments, a buffer device 15 is fixedly connected to the bottom of the main bag body 1, and the buffer device 15 comprises a buffer airbag and a gas generator, and the gas generator is rapidly inflated to expand the buffer airbag.
The buffer device can complete landing terrain identification and selection under the height of 3km according to a map image identification device and a rapid inflation unfolding device 21, provides navigation information of a target landing area for a flight control system, guides low-altitude controllable power to fly to the height of 300-500 m above the landing area to trigger a gas generator, rapidly inflates and unfolds the buffer air cushion, and achieves rapid deflation and safe recovery of the platform in soft landing.
In other embodiments, the system further comprises a measurement and control system, wherein the measurement and control system comprises a line-of-sight measurement and control terminal and a satellite measurement and control terminal, the line-of-sight measurement and control terminal and the satellite measurement and control terminal are arranged in the equipment cabin or on the surface of the main bag body, and the line-of-sight measurement and control terminal and the satellite measurement and control terminal provide a telemetering and remote control communication link for mutual backup of the line-of-sight and the beyond-sight of the boat. The position information of the airship is convenient to obtain.
Specifically, the lift gas is helium, hydrogen or a mixed gas of hydrogen and an inert gas, wherein the inert gas is an inert gas with a density less than that of air. Helium can be selected to provide lift force, and the device is safe to use.
More specifically, the gas storage device is spherical, is made of high-strength flexible composite materials, can be made of silicon rubber, has certain strength and good flexibility, can store certain buoyancy gas, has a diameter of 30m, and is hung at the top of the inner side of the main bag body through a restraint rope and a pull-mixing device.
In some embodiments, the equipment cabin and the energy cabin can be arranged at the lower part of the front annular framework to reduce the stress of the main bag body; the load cabin and the air supplement cabin can be arranged at the lower part of the middle annular framework, so that the stress of the main bag body is reduced, and the influence of different loads on the gravity center of the airship platform is avoided; the balance weight cabin can be distributed at the front section and the rear section of the main bag body and used for balancing the airship body, and the advantage of large longitudinal size force arm is utilized to efficiently balance and adjust the balance weight of the airship platform; the space size of each cabin body is adapted according to the layout of the internal electronic equipment; the air supply cabin can be selectively used, an air supply device is arranged in the air supply cabin, buoyancy lifting gas is stored in the air supply device, and the buoyancy lifting gas can be supplied into the main bag body under the condition of requirement.
The invention compresses the buoyancy gas in the main bag body into the gas storage device through the gas compressor or releases the buoyancy gas in the gas storage device into the main bag body through the dual-redundancy gas release valve, thereby realizing the bidirectional circulating pressure regulation of the buoyancy gas between the gas storage device and the main bag body, after the platform flight task is over, releasing a certain amount of buoyancy gas through the gas release valve to generate an initial descending speed, keeping the basic formation of the main bag body under the force bearing action of the supporting framework, forming a certain negative pressure area at the bottom of the main bag body, passively sucking air into the air bag through the one-way valve, continuously exciting the self-weight of the platform to increase and descend, and realizing the closed loop of the platform forming descending weight and the energy demand by only configuring a small amount of blowers to supplement the active air suction capacity.
According to the invention, by the aid of the buoyancy gas pressure adjusting device, large overpressure caused by hyperpyrexia of buoyancy gas is compressed into the gas storage device in daytime, so that overpressure safety of the main bag body is guaranteed; the buoyancy lifting gas is released into the main bag body at night, so that overpressure forming of the main bag body is guaranteed, and the problems of overpressure safety of the buoyancy bag body and buoyancy maintaining dimension caused by long-term idling of the platform and diurnal hyperthermia circulation are thoroughly solved. Meanwhile, the working pressure level of the main bag body is reduced, the low-pressure and low-leakage advantages of the buoyancy gas are better played, and the accessibility during overlong navigation is guaranteed.
The platform forming lifting can be realized by configuring a small amount of air release valves and blowers, and the energy and weight of the closed loop are restrained; the total amount of closed-loop energy and buoyancy lifting gas is not changed, and in addition, the air can be sucked and exhausted through the air bag to realize the adjustment of the air-holding height in the long-term air-holding task stage, so that the air-holding device has weak wind layer tracking capability; meanwhile, the supporting framework can assist in improving the low-pressure forming rigidity of the main bag body at night and the reliability of the installation of an external power system and a pod group, and the stability and the reliability of the ultra-long navigation are guaranteed more efficiently. After the task is executed, the floating gas is fed into the main capsule body again, and then the flight can be completed again. Can be repeatedly used.
The air bags are of an indefinite structure, can be distributed in a distributed mode, are communicated with one another, one air bag is communicated with the outside through a reserved flange interface on the main bag body, and an air blower and an air release valve are arranged at the communication position, so that the air suction and exhaust effects are achieved. Specifically, the air bag can reach 80% or more of the volume of the main bag body. The empennage adopts an X-shaped or inverted Y-shaped configuration and NACA 0012-NACA 0020 series airfoil profiles, the pneumatic action area accounts for more than 2% of the volume of the main bag body, and good pneumatic characteristics and operating characteristics are provided.
In the invention, the propeller is driven by the motor, the motor adopts a reduction drive or direct drive mode, the mounting and matching of the motor and the propeller are realized through the variable-pitch device, the power is matched, and the high-efficiency power output under various working conditions such as high altitude day, night, low altitude and the like can be compatible; the steering device adopts a motor to drive a reversing gear to realize active control of course, pitching and rolling postures of the sky-staying section and floating weight adjustment of the low-altitude landing stage, the head part, the tail part or the head part or the tail part can adopt course vector adjustment layout, and the power at two sides can adopt pitching vector adjustment layout.
The main bag body air release valve adopts a dual-redundancy and emergency cutting design, so that the reliable realization of the safety pressure regulation and air exhaust function is ensured. The compressor generally adopts two-stage compression, and the pressure head capacity is not less than 5000 Pa; the dual-redundancy air release valve has an emergency cutting function, and the reliable realization of the safety pressure regulation and air release function is ensured.
For the device and the using method disclosed by the embodiment, the description is simple because the device and the using method correspond to the method disclosed by the embodiment, and the relevant points can be referred to the description of the method part.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. A reciprocating stratospheric airship reusable during overlong navigation, comprising:
the airbag system comprises a main airbag body, an air bag and an empennage, wherein the main airbag body is of a streamline solid structure, the inner side wall of the main airbag body is fixedly connected with a supporting framework, and buoyancy gas is filled in the main airbag body; the air bag is fixed inside the main bag body, and air is filled in the air bag; the tail wing is arranged on the outer side of the tail end of the main bag body;
the pod group is fixed at the outer bottom of the main bag body; electronic equipment and energy equipment are arranged in the pod group;
the energy system comprises a solar cell array, an energy storage cell and an energy manager, wherein the solar cell array is fixed at the top of the outer side of the main bag body, and the energy storage cell is fixed in the pod group; the energy manager distributes and controls the working states of the energy equipment and the energy storage battery;
the power system comprises a propeller power device and a steering device for controlling the variable torque of the propeller, and the propeller power device and the steering device are both positioned at the tail end of the main bag body;
the pressure regulating system comprises a main bag body air release valve, an air bag air suction and exhaust device and a floating gas pressure regulating device, wherein the main bag body air release valve is fixed on the main bag body and used for releasing floating gas in the main bag body, and the air bag air suction and exhaust device is fixed on the outer side of the main bag body and communicated with the air bag through a pipeline to suck and exhaust air; the buoyancy gas pressure adjusting device comprises a gas storage device and a gas compressor, the gas storage device is fixed inside the main bag body and is provided with a gas inlet and a gas outlet, the gas inlet is connected with the gas compressor to press the buoyancy gas in the main bag body into the gas storage device, and the gas outlet is connected with a dual-redundancy gas release valve to release the buoyancy gas in the gas storage device so as to control the overpressure balance of the main bag body;
and the flight control system controls the propeller power device and the steering device through signals.
2. The back-and-forth type overlength stratospheric airship capable of being repeatedly used during navigation according to claim 1, wherein the length of the main bag body is 90-130 m, the slenderness ratio of the main bag body is 3-4, the main bag body is formed by laminating high-strength fabric and composite materials, the outer surface of the main bag body is provided with a thermal control coating, and the air bag is formed by processing a light high-elasticity film or a film bearing fabric material.
3. The back-and-forth type super-long-endurance and reusable stratospheric airship according to claim 1, wherein the pod group comprises an equipment cabin, an energy cabin, a counterweight cabin and a load cabin, the equipment cabin, the energy cabin, the counterweight cabin and the load cabin are all in a low-resistance streamline configuration or a fairing drag reduction configuration and are respectively fixed at the bottom of the outer side of the main capsule body, and the inner side walls of the equipment cabin and the energy cabin are provided with phase change material layers for controlling the temperature in the cabins.
4. The stratospheric airship with the repeated use during the round-trip type ultra-long voyage as claimed in claim 3, wherein the flight control system comprises a dual-redundancy high-performance computer, a combined inertial navigation device and a signal bus, the dual-redundancy high-performance computer is arranged in an equipment cabin, the combined inertial navigation device is arranged in the equipment cabin or on the outer surface of a main bag body, the signal bus is respectively connected with the combined inertial navigation device and the dual-redundancy high-performance computer, and the dual-redundancy high-performance computer realizes the remote measurement and control information management of a propeller power device and a steering device through embedded software.
5. The stratospheric airship with the air bag suction and exhaust device repeatedly usable during round-trip type overlength voyage as claimed in claim 1, wherein the air bag suction and exhaust device comprises an air release valve and an air blower, the air release valve is fixedly communicated with a bypass of a blower port of the air blower, a flange interface is reserved on the main bag body, the air bag is connected with the flange interface through a pipeline to realize the communication with the outside, the air blower and the air release valve are fixed on the outer side of the flange interface, the air bag releases the air in the air bag through the air release valve, and the air blower blows the air into the air bag to adjust the lifting of the main bag body.
6. The back-and-forth type overlength stratospheric airship capable of being repeatedly used during navigation according to claim 1, wherein the supporting framework comprises a circumferential framework, a longitudinal framework and tension cables, the circumferential framework and the longitudinal framework are respectively and fixedly connected to the inner side wall of the main bag body, the tension cables comprise a plurality of tension cables, and the tension cables are respectively and crossly tied on the circumferential framework.
7. The stratospheric airship of claim 1 and being reusable while reciprocating for very long voyage, wherein a buffer device is fixedly connected to the bottom of the main bag body, the buffer device comprises a buffer airbag and a gas generator, and the gas generator is rapidly inflated to expand the buffer airbag.
8. The stratospheric airship of claim 7, further comprising a measurement and control system, wherein the measurement and control system comprises a line-of-sight measurement and control terminal and a satellite measurement and control terminal, the line-of-sight measurement and control terminal and the satellite measurement and control terminal are arranged in an equipment cabin or on the surface of a main capsule, and the line-of-sight measurement and control terminal and the satellite measurement and control terminal provide a telemetering and remote control communication link for mutual backup of line-of-sight and over-line-of-sight of the airship.
9. The stratospheric airship of claim 1, wherein the buoyant gas is helium, hydrogen or a mixture of hydrogen and an inert gas, wherein the inert gas is an inert gas with a density less than air.
10. The stratospheric airship of claim 1, wherein the air storage device is spherical, made of high-strength flexible composite material, 10-30 m in diameter, and suspended on the top of the inner side of the main bag body through a restraining rope and a pull string.
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| CN202111579333.0A CN114104251A (en) | 2021-12-22 | 2021-12-22 | Reciprocating type stratospheric airship capable of being repeatedly used during overlong navigation |
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Application publication date: 20220301 |