CN104960657A - Combined-separate stratospheric aircraft system scheme - Google Patents
Combined-separate stratospheric aircraft system scheme Download PDFInfo
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- CN104960657A CN104960657A CN201510436462.2A CN201510436462A CN104960657A CN 104960657 A CN104960657 A CN 104960657A CN 201510436462 A CN201510436462 A CN 201510436462A CN 104960657 A CN104960657 A CN 104960657A
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Abstract
The invention provides a combined-separate stratospheric aircraft system scheme. The system scheme mainly comprises a high-altitude balloon, a solar powered unmanned air vehicle and a connecting rope, wherein the high-altitude balloon comprises a bag main body and a cable net structure which is outside the bag main body; and the solar powered unmanned air vehicle is the core of the whole platform and mainly comprises a structure subsystem, an energy subsystem, an avionic flight control subsystem, a propelling subsystem and a loading subsystem, which are arranged on a stabilizer of the solar powered unmanned air vehicle. According to the combined-separate stratospheric aircraft system scheme provided by the invention, the platform takes off through the high-altitude balloon; and the high-altitude balloon is separated from the solar powered unmanned air vehicle through an explosion device after the platform reaches a fixed flying height. The solar powered unmanned air vehicle flies for a long time through parts carried on the unmanned air vehicle and returns to a fixed point through its avionic flight control subsystem after the flying task is finished. Through the adoption of the combined-separate stratospheric aircraft system scheme provided by the invention, the performance of the solar powered unmanned air vehicle during executing the flying task can be greatly improved.
Description
Technical field
The invention provides a kind of combination separation type stratosphere flight device system schema, belong to aerospace plateform system technical field.
Background technology
Along with the further expansion in aerospace technology field, the stratosphere flight device used for Aeronautics and Astronautics joint portion has become the emphasis studied various countries.Compared with conventional airplane, the advantage of low speed stratosphere flight device is: (1) airborne period is long, sustainable work.Be easy to obtain information and data for a long time, incessantly, in time rapidly response made to emergency case.(2) wide coverage.The flying height of stratosphere flight device is larger than conventional airplane, and therefore coverage is also broader than conventional airplane.(3) viability is strong.Because the major part of balloon or blimp and some low-speed unmanned aerial vehicles adopts non-metallic material to make, therefore radar return cross section is very little, and traditional radar is difficult to follow the tracks of and find.(4) manufacture and operation and maintenance cost low, the support personnel of needs is few, logistic implications is light.
Compared with satellite, because stratosphere flight device runs highly low, general just low orbit satellite 1/10-1/20, easily realizes fine resolution earth observation, effectively can make up moonscope local blind spot.Require low to scouting, scope, adopt general digital camera, just may obtain the photo suitable with high precision satellite quality; Low cost of manufacture, does not need the launch facility of complex and expensive, lower to ground equipment requirement yet, and most of parts and the recyclable repeated usage of capacity weight, therefore efficiency-cost ratio is high.Emission process is comparatively simple; Capacity weight technical risk is little, is easy to upgrade and safeguard.
In the development process of stratosphere flight device, the solar power unmanned plane of HAE has become the focus of various countries' research.But the problem of existing research is: solar power unmanned plane rises to set flying height from ground, be generally 20km, the usual needs time of more than one day completes, and the problem that ascending velocity is brought slowly is that quick reaction capability is poor, and then affects the performance that it performs aerial mission.
For this reason, the present invention proposes a kind of combination separation type stratosphere flight device system schema, the program, by being filled with the quick lift-off of the aerostat implementation platform of helium, after arriving set flying height, realizing aerostat by demolition set and is separated with solar power unmanned plane.Solar power unmanned plane after separation performs aerial mission according to the avionics flight control system of self and carries out flight of giving an encore.
Summary of the invention
(1) object: the object of the present invention is to provide a kind of aerostat and the combined combination separation type stratosphere flight device system schema of solar power unmanned plane.The program utilizes the quick lift-off of aerostat implementation platform, after arriving set flying height, realizes aerostat be separated with solar power unmanned plane by demolition set.Solar power unmanned plane after separation performs aerial mission according to the avionics flight control system of self.
(2) technical scheme: the present invention's one combination separation type stratosphere flight device system schema, mainly comprises: aerostat, solar power unmanned plane, connecting rope; Wherein, aerostat part comprises again utricule body, the cable net structure of utricule outside; Solar power unmanned plane is the core of whole platform, primarily of the structure subsystem comprising body stabilator, and energy subsystem, avionics flies to control subsystem, propulsion subsystem, and load subsystem is formed;
Described utricule body adopts material that is cheap, lightweight to make, and is mainly used in storing helium, for whole platform provides effective lift;
The cable net structure of described utricule outside is mainly used in connecting solar power unmanned plane, and the lift that aerostat produces is supplied to solar power unmanned plane;
The described structure subsystem comprising body stabilator mainly provides the mounting interface of all airborne equipments on solar power unmanned plane;
Described energy subsystem is mainly the energy that whole platform provides required, and in addition, this system has energy management function concurrently;
Described avionics flies control subsystem and is mainly used in carrying out Real-Time Monitoring and control to the state of flight of whole platform;
Described propulsion subsystem is mainly used in coordinating the flight attitude of spheroid stabilator and body stabilator implementation platform to regulate and Route reform;
Described load subsystem is mainly used in realizing set aerial mission, as taken a picture, communicating.
The workflow of whole platform is as follows:
Under ground state, aerostat and solar power unmanned plane assembled respectively and debug complete, aerostat being inflated by set designing requirement, is connected with solar power unmanned plane by connecting rope after inflation completes;
Under initial condition, solar power unmanned plane head upward, by aerostat fast lifting to set flying height;
After reaching intended height, carry out length adjustment by the cable net structure on connecting rope and aerostat, solar power unmanned plane is evened up;
After solar power unmanned plane is evened up, start propulsion system, solar power unmanned plane is met and pushes away resistance balance under flight environment of vehicle;
After pushing away under solar power unmanned plane meets flight environment of vehicle hinders balance, the connection cord between aerostat and solar power unmanned plane will carry out explosion by demolition set, realize effective separation of two parts;
Operation flight when solar power unmanned plane utilizes self-contained parts to realize long;
After task completes, realize fixed point by the avionics flight control system of self and give an encore.
(3) advantage of the program: 1) this system profile layout is novel, inner structure is succinct, is easy to Project Realization; 2) load capacity promoting solar power unmanned plane is conducive to.Solar power unmanned plane is gone up to the air fast by the aerostat implementation platform being filled with helium, thus overcomes slow shortcoming of self going up to the air.Because solar power unmanned plane need not consider the problem of lift-off ability, therefore during design, the layout of single form more in the past increases by its load capacity; 3) be conducive to saving system energy.Under initial condition, solar power unmanned plane head, by aerostat fast lifting to set flying height, can reduce the resistance that goes up to the air upward like this, and then economize energy.
accompanying drawing illustrates:
Fig. 1 is that the present invention's one combination separation type stratosphere flight device system schema puts down integral structure figure when flying;
Fig. 2 is that the present invention's one combination separation type stratosphere flight device system schema puts down local structural graph when flying;
Integral structure figure when Fig. 3 is the stratosphere flight device system schema lift-off of the present invention's one combination separation type;
Local structural graph when Fig. 4 is the stratosphere flight device system schema lift-off of the present invention's one combination separation type;
Local structural graph when Fig. 5 is the stratosphere flight device system schema separation of the present invention's one combination separation type;
Number in the figure is described as follows:
1. aerostat, 2. cable net structure,
3. solar power unmanned plane, 4. body stabilator.
detailed description of the invention:
Below in conjunction with accompanying drawing, the present invention's one combination separation type stratosphere flight device system schema is further described:
The present invention's one combination separation type stratosphere flight device system schema, as shown in Fig. 1, mainly comprises aerostat 1, cable net structure 2, solar power unmanned plane 3, body stabilator 4.
As shown in Figure 3, Figure 4, in an embodiment of the present invention: under initial condition, when namely going up to the air, the rope connecting solar power unmanned plane 3 afterbody is transferred, and makes plane nose upward, and by aerostat 1 fast lifting to set flying height.Solar power unmanned plane head is conducive to reducing the lift-off resistance of whole system upward, and then can realize the requirement that aircraft goes up to the air fast.
As shown in Figure 1 and Figure 2, in an embodiment of the present invention: after platform reaches intended height, by carrying out length adjustment to the cable net structure on connecting rope and aerostat, solar power unmanned plane flies state by being become flat upward by original head.After this, start the propulsion system of solar power unmanned plane, solar power unmanned plane is met and pushes away resistance balance under flight environment of vehicle.
As shown in Figure 1, shown in Figure 5, in an embodiment of the present invention: after pushing away under solar power unmanned plane meets flight environment of vehicle hinders balance, the connection cord between aerostat and solar power unmanned plane will carry out explosion by demolition set, realize effective separation of two parts.Solar power unmanned plane after separation is performed aerial mission by the avionics flight control system of self and is realized fixed point and gives an encore.And the aerostat after being separated is low-cost production due to it, therefore do not consider to reclaim it.By above operation, the recycling of solar power unmanned plane can be realized.
It should be pointed out that this example only listing property application process of the present invention is described, but not for limiting the present invention.Any personnel being familiar with this kind of operation technique, all can without departing from the spirit and scope of the present invention, modify to above-described embodiment.Therefore, the scope of the present invention, should listed by claims.
Claims (3)
1. combine a separation type stratosphere flight device system schema, it is characterized in that: it mainly comprises: aerostat, solar power unmanned plane, connecting rope; Wherein, aerostat part comprises again utricule body, the cable net structure of utricule outside; Solar power unmanned plane is the core of whole platform, and primarily of the structure subsystem comprising body stabilator, energy subsystem, avionics flies to control subsystem, propulsion subsystem, and load subsystem is formed.
2. the one combination separation type stratosphere flight device system schema according to claims 1, is characterized in that: described utricule body adopts material that is cheap, lightweight to make, and is mainly used in storing helium, for whole platform provides effective lift;
The cable net structure of described utricule outside is mainly used in connecting solar power unmanned plane, and the lift that aerostat produces is supplied to solar power unmanned plane;
The described structure subsystem comprising body stabilator mainly provides the mounting interface of all airborne equipments on solar power unmanned plane;
Described energy subsystem is mainly the energy that whole platform provides required, and in addition, this system has energy management function concurrently;
Described avionics flies control subsystem and is mainly used in carrying out Real-Time Monitoring and control to the state of flight of whole platform;
Described propulsion subsystem is mainly used in coordinating the flight attitude of spheroid stabilator and body stabilator implementation platform to regulate and Route reform;
Described load subsystem is mainly used in realizing set aerial mission, as taken a picture, communicating.
3. the one combination separation type stratosphere flight device system schema according to claims 1, is characterized in that:
The workflow of whole platform is as follows:
Under ground state, aerostat and solar power unmanned plane assembled respectively and debug complete, aerostat being inflated by set designing requirement, is connected with solar power unmanned plane by connecting rope after inflation completes;
Under initial condition, solar power unmanned plane head upward, by aerostat fast lifting to set flying height;
After reaching intended height, carry out length adjustment by the cable net structure on connecting rope and aerostat, solar power unmanned plane is evened up;
After solar power unmanned plane is evened up, start propulsion system, solar power unmanned plane is met and pushes away resistance balance under flight environment of vehicle;
After pushing away under solar power unmanned plane meets flight environment of vehicle hinders balance, the connection cord between aerostat and solar power unmanned plane will carry out explosion by demolition set, realize effective separation of two parts;
Operation flight when solar power unmanned plane utilizes self-contained parts to realize long;
After task completes, realize fixed point by the avionics flight control system of self and give an encore.
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106155075A (en) * | 2016-08-22 | 2016-11-23 | 上海交通大学 | A kind of detachable unmanned aerial vehicle control system |
| CN106945839A (en) * | 2016-01-06 | 2017-07-14 | 吕智慧 | Flight instruments and its flying method |
| CN107499533A (en) * | 2017-07-07 | 2017-12-22 | 中国航空工业集团公司西安飞机设计研究所 | A kind of full machine drop test device and full machine drop-test method |
| CN108045543A (en) * | 2017-12-12 | 2018-05-18 | 中国科学院工程热物理研究所 | The jettison system of unmanned plane |
| CN108163181A (en) * | 2017-11-23 | 2018-06-15 | 北京天恒长鹰科技股份有限公司 | The recovery method of airship gondola, dirigible and airship gondola |
| CN108482634A (en) * | 2018-04-20 | 2018-09-04 | 中国气象局气象探测中心 | A kind of sounding balloon ball rope device for fusing |
| CN110435894A (en) * | 2019-07-03 | 2019-11-12 | 江汉大学 | A kind of aerial take-off system for solar energy unmanned plane |
| CN110920921A (en) * | 2019-10-30 | 2020-03-27 | 中国科学院光电研究院 | Near space aircraft launching system and method |
| CN110963041A (en) * | 2019-12-19 | 2020-04-07 | 中航电测仪器(西安)有限公司 | Method for flying fixed-wing aircraft based on helicopter hanging and delivering system |
| CN112173123A (en) * | 2020-10-16 | 2021-01-05 | 西京学院 | Logistics express transportation system and method for nuclear-powered non-landing aircraft |
| CN112623179A (en) * | 2020-12-23 | 2021-04-09 | 中国科学院力学研究所 | Recoverable flexible formula transmission nacelle |
| CN112918656A (en) * | 2021-02-26 | 2021-06-08 | 中国航天空气动力技术研究院 | High-altitude spherical solar unmanned aerial vehicle system |
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| CN109141429B (en) * | 2018-09-03 | 2021-08-03 | 中国科学院工程热物理研究所 | Method for designing flight path of near space ball-borne solar unmanned aerial vehicle in throwing process |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107499533A (en) * | 2017-07-07 | 2017-12-22 | 中国航空工业集团公司西安飞机设计研究所 | A kind of full machine drop test device and full machine drop-test method |
| CN108163181A (en) * | 2017-11-23 | 2018-06-15 | 北京天恒长鹰科技股份有限公司 | The recovery method of airship gondola, dirigible and airship gondola |
| CN108045543A (en) * | 2017-12-12 | 2018-05-18 | 中国科学院工程热物理研究所 | The jettison system of unmanned plane |
| CN108482634A (en) * | 2018-04-20 | 2018-09-04 | 中国气象局气象探测中心 | A kind of sounding balloon ball rope device for fusing |
| CN110435894A (en) * | 2019-07-03 | 2019-11-12 | 江汉大学 | A kind of aerial take-off system for solar energy unmanned plane |
| CN110920921A (en) * | 2019-10-30 | 2020-03-27 | 中国科学院光电研究院 | Near space aircraft launching system and method |
| CN110920921B (en) * | 2019-10-30 | 2022-08-30 | 中国科学院光电研究院 | Near space aircraft launching system and method |
| CN110963041A (en) * | 2019-12-19 | 2020-04-07 | 中航电测仪器(西安)有限公司 | Method for flying fixed-wing aircraft based on helicopter hanging and delivering system |
| CN112173123A (en) * | 2020-10-16 | 2021-01-05 | 西京学院 | Logistics express transportation system and method for nuclear-powered non-landing aircraft |
| CN112623179A (en) * | 2020-12-23 | 2021-04-09 | 中国科学院力学研究所 | Recoverable flexible formula transmission nacelle |
| CN112918656A (en) * | 2021-02-26 | 2021-06-08 | 中国航天空气动力技术研究院 | High-altitude spherical solar unmanned aerial vehicle system |
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