CN102442432A - Combination type high-altitude precise aerial delivery system - Google Patents
Combination type high-altitude precise aerial delivery system Download PDFInfo
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- CN102442432A CN102442432A CN2011103462085A CN201110346208A CN102442432A CN 102442432 A CN102442432 A CN 102442432A CN 2011103462085 A CN2011103462085 A CN 2011103462085A CN 201110346208 A CN201110346208 A CN 201110346208A CN 102442432 A CN102442432 A CN 102442432A
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Abstract
The invention relates to a combination type high-altitude precise aerial delivery system, which is composed of a controllable parafoil aircraft assembly, a detachable power assembly and a detachable round parachute assembly. After being delivered in high altitude, the system is controlled autonomously and lands on a destination safely and precisely. When both the flying environment and the landing environment are good, the controllable parafoil aircraft assembly is only used to execute a task, thus, the flying weight of the system is lightened, and the system is simplified. The controllable parafoil aircraft assembly and the detachable power assembly are combined, thus, the system can be applied to a severe flying environment; furthermore, the flying delivery distance can also be prolonged. The controllable parafoil aircraft assembly and the detachable round parachute assembly are combined, thus, the round parachute can be opened when the system reaches a low-altitude airspace of a landing point to realize ease landing, and, the system can be applied to a severe landing environment. The controllable parafoil aircraft assembly, the detachable power assembly and the detachable round parachute assembly are combined, thus, the system can be applied to the severe flying environment; the flying delivery distance can be prolonged; furthermore, the system can be applied to the sever landing environment to realize the ease landing. The system disclosed by the invention is multifunctional and wide in application range.
Description
Technical field
The present invention is a kind of compound type high-altitude precision aerial delivery system, belongs to the technical field of structures of aircraft.
Background technology
Need goods and materials to replenish in the operation front, or disaster ground to use accurate aerial delivery system that goods and materials are shipped to the destination when needing goods and materials to rescue usually.At present, domestic and international widely used aerial delivery system has two kinds, the controlled parasail of the first, and like " onyx " self-contained guidance paraglider system of the U.S. etc., it two is circular parachutes.Though controlled parasail flight course is controlled, because its umbrella blade area is restricted, the landing impulsive force is big, and because the landing conditional request is high, when meeting with abominable landing environment, goods and materials are impaired easily; Controlled parasail is drive not, and especially when meeting with abominable flight environment of vehicle, flying distance is reduced greatly, goods and materials often takes place deliver the situation less than the destination; Though circular parachute umbrella blade area is big, the landing impulsive force is little, and its heading is uncontrollable, loses air-dropped material easily.
Summary of the invention
The present invention designs to the deficiency that exists in the above-mentioned prior art just a kind of compound type high-altitude precision aerial delivery system is provided; Its objective is conditions such as atmosphere image data, air-drop distance and drop altitude through analyzing the air-drop environment; Take array mode to prepare to carry-on assembly to be applicable to various aerial missions; Realization can be simple and reliable, in light weight, can satisfy the requirement of airdrop mission again, formulates the flight scheme; Throw in the back by system's Autonomous Control from the high-altitude, and safely, accurately drop to the destination.
The objective of the invention is to realize through following technical scheme:
This kind compound type high-altitude precision aerial delivery system; Mainly comprise fuselage, bikini alighting gear, personal vehicle system and controlled parafoil assembly; It is characterized in that: controlled parafoil assembly is made up of glide parafoil umbrella head, glide parafoil rope, glide parafoil umbrella cabin, control wire controller and control wire; Glide parafoil umbrella head is kept the In-Flight Deployment form by glide parafoil rope; Glide parafoil umbrella cabin is installed on the fuselage, and its opening device and personal vehicle system are implemented control through cable connection and by personal vehicle system, and the control wire controller is installed in the both sides of fuselage; Also spur two groups of control wires through the cable connection personal vehicle system and by personal vehicle system control control wire controller, control wire affects the flight attitude of the left and right sides trailing edge of glide parafoil umbrella head with control glide parafoil umbrella head.
According to different environments for use; With above-mentioned controlled parafoil assembly and fuselage part as the main body flight system; Rear end at fuselage can be installed removable screw propeller power propeller again, and the screw propeller periphery of power propeller is equipped with the back up ring, is combined into a new flight system.
Equally; According to different environments for use; Above-mentioned controlled parafoil assembly and fuselage part as the main body flight system, can be installed removable round umbrella umbrella cabin again on fuselage, keep its skyborne shape through circle umbrella umbrella rope by the circular parachute that circle umbrella umbrella cabin discharges; The opening device and the personal vehicle system in circle umbrella umbrella cabin are implemented control through cable connection and by personal vehicle system, are combined into another new flight system.
Can also above-mentioned screw propeller power propeller and circle umbrella umbrella cabin be installed in controlled parafoil assembly and fuselage simultaneously partly as in the main body flight system, constitute most complete flight system.
In a word, characteristics of the present invention are to realize each assembly module design, can each assembly independent assortment quickly neither be wasted the use of unnecessary resource, and system is simplified and to reach reliability the highest as far as possible, can make up each component function again to satisfy mission requirements.
Description of drawings
Fig. 1 is the flight course scheme drawing of flight system of the present invention
Fig. 2 is the scheme drawing of controlled parafoil assembly in the system of the present invention and Power Component combination
Fig. 3 is the right elevation of Fig. 2;
Fig. 4 makes up scheme drawing for controlled parafoil assembly in the system of the present invention and Power Component, circle umbrella assembly
The specific embodiment
Below will combine accompanying drawing and embodiment that technical scheme of the present invention is done to detail further:
Shown in accompanying drawing 1～4; This kind compound type high-altitude precision aerial delivery system; Mainly comprise fuselage 4, bikini alighting gear 8, personal vehicle system 3 and controlled parafoil assembly; It is characterized in that: controlled parafoil assembly is made up of glide parafoil umbrella head 1, glide parafoil rope 2, glide parafoil umbrella cabin 6, control wire controller 7 and control wire 5; Glide parafoil umbrella head 1 is kept the In-Flight Deployment form by glide parafoil rope 2; Glide parafoil umbrella cabin 6 is installed on the fuselage 4, and its opening device and personal vehicle system 3 are implemented control through cable connection and by personal vehicle system 3, and control wire controller 7 is installed in the both sides of fuselage 4; Also through cable connection personal vehicle system 3 and by two groups of control wires 5 of personal vehicle system 3 control control wire controller 7 pullings, control wire 5 affects the flight attitude of the left and right sides trailing edge of glide parafoil umbrella head 1 with control glide parafoil umbrella head 1.
Screw propeller power propeller 10 is installed in rear end at fuselage 4, and the screw propeller periphery of power propeller 10 is equipped with back up ring 9.
Round umbrella umbrella cabin 13 is installed on fuselage 4, keeps its skyborne shape by the circular parachute 11 that circle umbrella umbrella cabin 13 discharges through circle umbrella umbrella rope 12, the opening device and the personal vehicle system 3 in circle umbrella umbrella cabin 13 are implemented control through cable connection and by personal vehicle system 3.
After the input of high-altitude, by the control of each unit in the personal vehicle system 3 execution flight scheme processes, there is the parachute opener in parachute opener, control wire controller 7, power propeller 10 and the circle umbrella umbrella cabin 13 in glide parafoil umbrella cabin 6 unit of major control.Before air-drop; Glide parafoil umbrella head 1, glide parafoil umbrella rope 2 and the control wire 5 folding glide parafoil umbrella cabins 6 of putting into; After putting down from the aircraft upslide; By the parachute opener in personal vehicle system 3 control glide parafoil umbrella cabins 6, at a time between section glide parafoil umbrella head 1 and glide parafoil umbrella rope 2 are discharged, and through aerodynamic force with 1 expansion of glide parafoil umbrella head.By glide parafoil umbrella head 1 aerodynamic lift is provided in-flight.By two control wires 5 about control wire controller 7 pulling, control wire 5 affects the left and right sides trailing edge of glide parafoil umbrella head 1 to make its distortion in-flight, causes the variation of aerodynamic force by the distortion of glide parafoil umbrella head 1, thus the flight attitude of controlling aircraft.With dismantled and assembled Power Component and controlled parafoil combination of components the time; Be the structure of screw propeller back up ring 9 and power propeller 10 and the structure of fuselage 4 to be linked together through simple bolt mounting means; And automatically controlled group of power propeller 10 is linked together with personal vehicle system through electronic connector; By the power size of personal vehicle system 3 control Power Component medium power propelling units 10, thereby influence flight attitude.With dismantled and assembled round umbrella assembly and controlled parafoil combination of components the time; Be circular parachute head 11 to be folded up with circle umbrella umbrella rope 12 put into round umbrella umbrella cabin 13; To justify umbrella umbrella cabin 13 again is installed in above the fuselage 4 through bolt; The parachute opener in personal vehicle system 3 control circle umbrella umbrella cabins 13 discharges circular parachute head 11 and circle umbrella umbrella rope 12 in certain time period that arrives spatial domain, low latitude, level point, and through aerodynamic force circular parachute head 11 is launched; The pneumatic buffer power that circular parachute head 11 produces has been slowed down the falling speed of aircraft, thereby reaches the purpose that relaxes landing.
Under flight environment of vehicle and all good condition of landing environment, only use controlled parafoil assembly to execute the task, do not increase unnecessary assembly, so that the flying weight of mitigation system, simplified system improves the system reliability coefficient.Under the flight environment of vehicle condition of severe,, for system provides forward thrust, can prolong flying distance, the landing scope of guaranteeing to fly with controlled parafoil assembly and the combination of dismantled and assembled Power Component.Under the abominable or unknowable situation of landing environment, with controlled parafoil assembly and dismantled and assembled round umbrella assembly combination, system can open round umbrella when arriving spatial domain, low latitude, level point, realize relaxing and land, and guarantees that air-dropped material is injury-free at the landing environment.With three combination of components, not only can adapt to abominable flight environment of vehicle, prolong flight and throw in distance, can also adapt to abominable landing environment, realize relaxing landing.
As shown in Figure 1, system of the present invention experiences four-stage altogether in that controlled parafoil assembly and dismantled and assembled Power Component, dismantled and assembled round umbrella assembly are combined as among the embodiment of system's execution airdrop mission.1. freight house is launched in the high-altitude by system before this; 2. system opens glide parafoil umbrella head and carries out gliding flight then; 3. system meets with severe weather conditions so that can't glide when landing scope; Start Power Component correction course line, open the umbrella head of round umbrella assembly when 4. arriving spatial domain, low latitude, level point at last and realize relaxing landing.
Compared with prior art; The present invention had both solved the problem that conventional controlled parasail can't reach the destination meeting with abominable flight environment of vehicle; Solved the problem that conventional controlled parasail can't safe falling meeting with abominable landing environment again, solved also that conventional circular parachute can not be controlled heading and the problem of losing goods and materials.
Claims (3)
1. compound type high-altitude precision aerial delivery system; Mainly comprise fuselage (4), bikini alighting gear (8), personal vehicle system (3) and controlled parafoil assembly; It is characterized in that: controlled parafoil assembly is made up of glide parafoil umbrella head (1), glide parafoil rope (2), glide parafoil umbrella cabin (6), control wire controller (7) and control wire (5); Glide parafoil umbrella head (1) is kept the In-Flight Deployment form by glide parafoil rope (2); Glide parafoil umbrella cabin (6) is installed on the fuselage (4); Its opening device and personal vehicle system (3) are implemented control through cable connection and by personal vehicle system (3); Control wire controller (7) is installed in the both sides of fuselage (4), and also through cable connection personal vehicle system (3) and by personal vehicle system (3) control control wire controller (7) pulling two groups of control wires (5), control wire (5) affects the flight attitude of the left and right sides trailing edge of glide parafoil umbrella head (1) with control glide parafoil umbrella head (1).
2. compound type according to claim 1 high-altitude precision aerial delivery system is characterized in that: screw propeller power propeller (10) is installed in the rear end at fuselage (4), and the screw propeller periphery of power propeller (10) is equipped with back up ring (9).
3. compound type according to claim 1 high-altitude precision aerial delivery system; It is characterized in that: round umbrella umbrella cabin (13) is installed on fuselage (4); Circular parachute (11) by circle umbrella umbrella cabin (13) discharges is kept its skyborne shape through circle umbrella umbrella rope (12), and the opening device in circle umbrella umbrella cabin (13) and personal vehicle system (3) are implemented control through cable connection and by personal vehicle system (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN2011103462085A CN102442432A (en) | 2011-11-04 | 2011-11-04 | Combination type high-altitude precise aerial delivery system |
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| CN2011103462085A CN102442432A (en) | 2011-11-04 | 2011-11-04 | Combination type high-altitude precise aerial delivery system |
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| CN102442432A true CN102442432A (en) | 2012-05-09 |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103101621A (en) * | 2013-01-22 | 2013-05-15 | 北京航空航天大学 | Parafoil aircraft applicable to cylindrical space loading |
| CN103332291A (en) * | 2013-06-14 | 2013-10-02 | 南京航空航天大学 | Folding and unfolding mechanism for air-drop hex-rotor wing unmanned aerial vehicle |
| CN104677662A (en) * | 2015-02-10 | 2015-06-03 | 中国工程物理研究院总体工程研究所 | Non-stabilized projectile airdrop parachute-opening simulation test device and test method |
| CN105438465A (en) * | 2015-12-15 | 2016-03-30 | 中国科学院合肥物质科学研究院 | Novel gliding type bionic air-drop device |
| CN106081090A (en) * | 2016-08-16 | 2016-11-09 | 中国工程物理研究院总体工程研究所 | Flex-wing controllable platform during long boat |
| CN106326578A (en) * | 2016-08-26 | 2017-01-11 | 北京航天控制仪器研究所 | Method for determining airdrop initial area of precise airdrop system |
| WO2018020500A1 (en) * | 2016-07-28 | 2018-02-01 | Urban Aeronautics, Ltd | System and method for automated landing of a parachute-suspended body |
| CN107745814A (en) * | 2017-11-15 | 2018-03-02 | 航宇救生装备有限公司 | A kind of active landed for aerial delivery system is anti-to turn over controlling organization |
| CN108945464A (en) * | 2018-08-23 | 2018-12-07 | 广州创链科技有限公司 | A kind of shipping unmanned plane cargo assault operation carrying cabin |
| CN110844045A (en) * | 2019-10-31 | 2020-02-28 | 湖南航天机电设备与特种材料研究所 | Long-range accurate air-drop equipment that glides |
| CN114180073A (en) * | 2022-02-16 | 2022-03-15 | 四川腾盾科技有限公司 | Parachute opening mechanism and delay parachute opening method for pod of unmanned aerial vehicle |
| CN115848672A (en) * | 2023-02-15 | 2023-03-28 | 北京瀚科智翔科技发展有限公司 | Open-type hollow structure freight transport unmanned aerial vehicle with packaging air-drop capability |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4601443A (en) * | 1982-09-30 | 1986-07-22 | Jones Andrew W | Free flyable structure |
| WO1993001087A1 (en) * | 1991-07-01 | 1993-01-21 | Snyder Stephen Louis | Airfoil canopy aircraft |
| US20030218099A1 (en) * | 2001-12-07 | 2003-11-27 | Daniel Preston | Multimodal, deployable vehicle |
| CN201534615U (en) * | 2009-05-08 | 2010-07-28 | 王硕 | Accurate air-dropping device |
| CN102183961A (en) * | 2011-04-08 | 2011-09-14 | 张璞 | Digital positioning landing control device |
-
2011
- 2011-11-04 CN CN2011103462085A patent/CN102442432A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4601443A (en) * | 1982-09-30 | 1986-07-22 | Jones Andrew W | Free flyable structure |
| WO1993001087A1 (en) * | 1991-07-01 | 1993-01-21 | Snyder Stephen Louis | Airfoil canopy aircraft |
| US20030218099A1 (en) * | 2001-12-07 | 2003-11-27 | Daniel Preston | Multimodal, deployable vehicle |
| CN201534615U (en) * | 2009-05-08 | 2010-07-28 | 王硕 | Accurate air-dropping device |
| CN102183961A (en) * | 2011-04-08 | 2011-09-14 | 张璞 | Digital positioning landing control device |
Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103101621B (en) * | 2013-01-22 | 2015-03-25 | 北京航空航天大学 | Parafoil aircraft applicable to cylindrical space loading |
| CN103101621A (en) * | 2013-01-22 | 2013-05-15 | 北京航空航天大学 | Parafoil aircraft applicable to cylindrical space loading |
| CN103332291A (en) * | 2013-06-14 | 2013-10-02 | 南京航空航天大学 | Folding and unfolding mechanism for air-drop hex-rotor wing unmanned aerial vehicle |
| CN103332291B (en) * | 2013-06-14 | 2015-11-18 | 南京航空航天大学 | A kind of air-drop six rotor wing unmanned aerial vehicles fold and development mechanism |
| CN104677662A (en) * | 2015-02-10 | 2015-06-03 | 中国工程物理研究院总体工程研究所 | Non-stabilized projectile airdrop parachute-opening simulation test device and test method |
| CN104677662B (en) * | 2015-02-10 | 2017-03-08 | 中国工程物理研究院总体工程研究所 | Unstable body air-drop parachute-opening simulation test device and test method |
| CN105438465A (en) * | 2015-12-15 | 2016-03-30 | 中国科学院合肥物质科学研究院 | Novel gliding type bionic air-drop device |
| WO2018020500A1 (en) * | 2016-07-28 | 2018-02-01 | Urban Aeronautics, Ltd | System and method for automated landing of a parachute-suspended body |
| CN106081090B (en) * | 2016-08-16 | 2019-01-11 | 中国工程物理研究院总体工程研究所 | Long endurance flex-wing controllable platform |
| CN106081090A (en) * | 2016-08-16 | 2016-11-09 | 中国工程物理研究院总体工程研究所 | Flex-wing controllable platform during long boat |
| CN106326578A (en) * | 2016-08-26 | 2017-01-11 | 北京航天控制仪器研究所 | Method for determining airdrop initial area of precise airdrop system |
| CN106326578B (en) * | 2016-08-26 | 2019-07-12 | 北京航天控制仪器研究所 | A kind of precision aerial delivery system air-drop prime area determines method |
| CN107745814A (en) * | 2017-11-15 | 2018-03-02 | 航宇救生装备有限公司 | A kind of active landed for aerial delivery system is anti-to turn over controlling organization |
| CN107745814B (en) * | 2017-11-15 | 2023-12-22 | 航宇救生装备有限公司 | Active anti-overturning control mechanism for landing of air drop system |
| CN108945464A (en) * | 2018-08-23 | 2018-12-07 | 广州创链科技有限公司 | A kind of shipping unmanned plane cargo assault operation carrying cabin |
| CN108945464B (en) * | 2018-08-23 | 2020-09-08 | 叶加军 | Cargo transport unmanned aerial vehicle material air-drop operation bearing cabin |
| CN110844045A (en) * | 2019-10-31 | 2020-02-28 | 湖南航天机电设备与特种材料研究所 | Long-range accurate air-drop equipment that glides |
| CN114180073A (en) * | 2022-02-16 | 2022-03-15 | 四川腾盾科技有限公司 | Parachute opening mechanism and delay parachute opening method for pod of unmanned aerial vehicle |
| CN114180073B (en) * | 2022-02-16 | 2022-05-03 | 四川腾盾科技有限公司 | Parachute opening mechanism and delay parachute opening method for pod of unmanned aerial vehicle |
| CN115848672A (en) * | 2023-02-15 | 2023-03-28 | 北京瀚科智翔科技发展有限公司 | Open-type hollow structure freight transport unmanned aerial vehicle with packaging air-drop capability |
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Application publication date: 20120509 |