CN1203167A - Manned aerobat capable of landing or taking-off vertically - Google Patents
Manned aerobat capable of landing or taking-off vertically Download PDFInfo
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- CN1203167A CN1203167A CN 97112823 CN97112823A CN1203167A CN 1203167 A CN1203167 A CN 1203167A CN 97112823 CN97112823 CN 97112823 CN 97112823 A CN97112823 A CN 97112823A CN 1203167 A CN1203167 A CN 1203167A
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- slide rail
- host wing
- aviator
- pipe link
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Abstract
A manned vertical-takeoff and landing flight vehicle is composed of slide track, electric track-sliding apparatus, principal wing, engine, manipulating arms and control handle, and features that it is suitable for person takeoff and landing flying in vertical and conventional horizontal flying, and the transition flying between them.
Description
The present invention relates to the manned aerobat capable of landing or taking-off vertically technical field.
In the prior art with the present invention nearer like two kinds of designs, a kind of is the V-22 vertical takeoff and landing (VTOL) experimental engine of the U.S., a kind of is the AV-8B sparrow hawk formula VTOL fighter of Britain, is introduced respectively below:
1, V-22, it is a kind of design of bionics preferably, it provides power and lift by two convertible engines that are located at the wing edge, driving engine produces application force downwards or backward for rotatable 90 °, propeller blade is by offsetting the twisting resistance that produces mutually to changeing, transverse center of gravity with two downward application force pull-up bodies makes the vertical built on stilts of body, turn to generation application force backward by driving engine then, finish from taking off vertically to the flat transition that flies of routine, it and orthodox flight device almost are as good as in view of speed and voyage, are a kind of very effective designs.
2, AV-8B, be a kind of very practical vertical takeoff and landing (VTOL) fighter jet, it stably props the transverse center of gravity of body with four force positions, after the certain distance of body disengaging ground, driving engine begins to be transferred back, and aircraft is crossed to flat the flying over of routine from the state of taking off vertically.
Design of the present invention and above two kinds of design-calculated something in commons are all to design vertical takeoff and landing and the conventional flat switch transition that flies, but also be essentially different between the design and above two kinds of designs, more than two kinds of designs take off vertically that what boost is the transverse center of gravity point, what application force was propped is a plane, so need two driving engines at least,, then must design at the top that is applied thing if having only two driving engines, even so also unstable, can rock back and forth.The design takes off vertically, and what boost is the vertical focus point of flying body, the application force pull-up be straight line, so only need more than one driving engine just enough.
The purpose of this invention is to provide a kind of center of gravity direction that can change people and aircraft, promptly realize the switch transition between vertical center of gravity and transverse center of gravity, thereby realize the switch transition between vertical takeoff and landing and conventional flat flying, physiological structure characteristics design at the people, performance utilizes people's physiological structure characteristics to greatest extent, the manned aerobat capable of landing or taking-off vertically of compact, the most suitable people's flight of structure.
Technical conceive of the present invention is:
Physiological structure characteristics design at the people, make people's physiological structure characteristics obtain utilizing to greatest extent, the most suitable people's flight requirement, the design-calculated key is to change the center of gravity direction of people or flying body, promptly realize the switch transition between vertical center of gravity and transverse center of gravity, thereby realize the switch transition between vertical takeoff and landing and conventional flat flying.
Power on acting on longitudinal center of gravity point B＞when acting on the power on the transverse center of gravity point A, flying body and people are in the vertical takeoff and landing state;
Power on acting on longitudinal center of gravity point B 〉=≤when acting on the power on the transverse center of gravity point A, flying body and people are in the transition condition between vertical takeoff and landing and conventional flat flying;
Power on acting on longitudinal center of gravity point B≤when acting on the power on the transverse center of gravity point A, flying body and people are in conventional flat state or the basic flat state that flies of flying.
Technical scheme of the present invention is:
This novel manned aerobat capable of landing or taking-off vertically comprises fixedly major parts such as braces, clamping band, slide rail, electronic slide rail device, host wing, driving engine, control arm, bar handle, empennage; Wherein fixedly braces is two, be separately fixed on the slide rail, the aviator back of the body carry two fixedly braces slide rail carried on the back put at back, on slide rail, also be provided with the plurality of fixed band, slide rail firmly is strapped on one's body the aviator, host wing links to each other with slide rail by electronic slide rail device, the aerofoil of host wing is parallel to aviator's health plane, on the host wing with the line of centers of host wing for being symmetrically arranged with two driving engines, the fuel oil of flight usefulness is stored in the host wing, be provided with two control arms at the top of host wing, the other end of two control arms all is positioned at the aviator front, and this end is equipped with bar handle, and each fixes an empennage at aviator's shank place, empennage aerofoil and aviator's health plane parallel; Slide rail, electronic slide rail device, connection between the wing: electronic slide rail device one end embeds in the slide rail, electronic this end of slide rail device is provided with some pulleys, one group of pulley is positioned on the external slideway of slide rail, another group pulley is positioned on the inner slide of slide rail, be provided with synchronous dynamo in the electronic slide rail device, synchronous dynamo driven gear group, thereby drive one and change the line wheel, also be provided with one and change the line wheel, pulley affects steel wire one end to be fixed on an end of slide rail, the other end becomes the figure of eight to walk around two changes the line wheel, be fixed on the slide rail other end then, the other end of electronic slide rail device becomes point or circular arc pointed, be positioned at the spill guide groove on the host wing aerofoil, and link to each other with host wing with pipe link, pipe link is positioned at the groove of host wing, also be provided with spring in the groove, spring one end links to each other with pipe link, the other end is connected in pipe link far away one end of groove, the end that pipe link links to each other with spring also is connected with pipe link and affects steel wire, affect the other end of steel wire to pull out outside the host wing, affect bar to link to each other with pipe link, pipe link affects bar and control arm to be fixed together;
Control part adopts reversible PWM amplifirer speed system, from+V,-V holds a given incoming signal and the feedback speed signal addition that records through tachogenerator to send into 1 end of preamplifier K1, the 2 end ground connection of K1, the speed signal that records through tachogenerator feeds back to the corrective loop simultaneously, 1 end that the signal plus of signal after the correction and the output of K1 mouth is sent into K2 amplifies once more, proofread and correct output simultaneously, the 2 end ground connection of K2, the amplifying signal of K2 mouth output inserts 2 ends of comparator A, the signal that triangular-wave generator produces inserts 1 end of comparator A, the triangular signal addition that the amplifying signal of K2 output and triangular-wave generator produce produces modulated pulse signal to the circuit in logical delay through comparator A, and logical delay, circuit was divided into four tunnel logic control impulse singlas with modulating pulse: logical delay, circuit output end 1 was to EVK31-050
1,-1-AX, logical delay, circuit 3 was to EVK31-050
1-3-AY, logical delay, circuit output end 4 was to EVK31-051
2-4-BY, logical delay, circuit output end 2 was to EVK31-050
2-2-BX.
Below in conjunction with drawings and Examples the present invention is done description in further detail:
Fig. 1 is the front view of manned aerobat capable of landing or taking-off vertically of the present invention;
Fig. 2 is the lateral plan of manned aerobat capable of landing or taking-off vertically of the present invention;
Fig. 3 is the birds-eye view of manned aerobat capable of landing or taking-off vertically of the present invention;
Fig. 4 is the block diagram of manned aerobat capable of landing or taking-off vertically of the present invention;
Fig. 5 is the slide rail and the electronic slide rail device connection diagram of manned aerobat capable of landing or taking-off vertically of the present invention;
Fig. 6 is the slide rail and the electronic slide rail device bonded assembly A-A cutaway view of manned aerobat capable of landing or taking-off vertically of the present invention;
Fig. 7 is the condenser electricity firing circuit schematic diagram of the driving engine of manned aerobat capable of landing or taking-off vertically of the present invention;
Fig. 8 is the control part schematic circuit diagram of manned aerobat capable of landing or taking-off vertically of the present invention;
Fig. 9 is the take-off process scheme drawing of manned aerobat capable of landing or taking-off vertically of the present invention;
Figure 10 is the landing mission scheme drawing of manned aerobat capable of landing or taking-off vertically of the present invention;
Figure 11 is the escape process scheme drawing of manned aerobat capable of landing or taking-off vertically et out of order of the present invention.
It comprises fixedly major parts such as braces 7, clamping band 8, slide rail 11, electronic slide rail device 16, host wing 6, driving engine 5, control arm 4, bar handle 1, empennage 10; Wherein fixedly braces 7 is two, be separately fixed on the slide rail 11, the aviator back of the body carry two fixedly braces 7 slide rail 11 carried on the back put at back, on slide rail 11, also be provided with plurality of fixed band 8, slide rail 11 firmly is strapped on one's body the aviator, host wing 6 links to each other with slide rail 11 by electronic slide rail device 16, the aerofoil of host wing 6 is parallel to aviator's health plane, on the host wing 6 with the line of centers of host wing 6 for being symmetrically arranged with two driving engines 5, the fuel oil of flight usefulness is stored in the host wing 6, be provided with two control arms 4 at the top of host wing 6, the other end of two control arms 4 all is positioned at the aviator front, and this end is equipped with bar handle 1, and each fixes an empennage 10 at aviator's shank place, empennage 10 aerofoils and aviator's health plane parallel; Slide rail 11, electronic slide rail device 16, connection between the wing 6: electronic slide rail device 16 1 ends embed in the slide rail 11, electronic slide rail device 16 these ends are provided with some pulleys 19, one group of pulley 19 is positioned on the external slideway 24 of slide rail 11, another group pulley 19 is positioned on the inner slide 25 of slide rail 11, be provided with synchronous dynamo 14 in the electronic slide rail device 16, synchronous dynamo 14 driven gear groups 15, thereby drive one and change line wheel 17, also be provided with one and change line wheel 17, pulley affects steel wire 18 1 ends to be fixed on an end of slide rail 11, the other end becomes the figure of eight to walk around two changes line wheel 17, be fixed on slide rail 11 other ends then, the other end of electronic slide rail device 16 becomes point or circular arc pointed, be positioned at the spill guide groove 13 on host wing 6 aerofoils, and link to each other with host wing 6 with pipe link 13, pipe link 13 is positioned at the groove 26 of host wing 6, also be provided with spring 21 in the groove, spring 21 1 ends link to each other with pipe link 13, the other end is connected in pipe link far away 13 1 ends of groove 26, the end that pipe link 13 links to each other with spring 21 also is connected with pipe link and affects steel wire 22, affect the other end of steel wire 22 to pull out outside the host wing 6, affect bar 23 to link to each other with pipe link, pipe link affects bar 23 and control arm 4 to be fixed together; Control part adopts reversible PWM amplifirer speed system, from+V,-V holds a given incoming signal and the feedback speed signal addition that records through tachogenerator to send into 1 end of preamplifier K1, the 2 end ground connection of K1, the speed signal that records through tachogenerator feeds back to the corrective loop simultaneously, 1 end that the signal plus of signal after the correction and the output of K1 mouth is sent into K2 amplifies once more, proofread and correct output simultaneously, the 2 end ground connection of K2, the amplifying signal of K2 mouth output inserts 2 ends of comparator A, the signal that triangular-wave generator produces inserts 1 end of comparator A, the triangular signal addition that the amplifying signal of K2 output and triangular-wave generator produce produces modulated pulse signal to the circuit in logical delay through comparator A, and logical delay, circuit was divided into four tunnel logic control impulse singlas with modulating pulse: logical delay, circuit output end 1 was to EVK31-050
1-1-AX, logical delay, circuit 3 was to EVK31-050
1-3-AY, logical delay, circuit output end 4 was to EVK31-051
2-4-BY, logical delay, circuit output end 2 was to EVK31-050
2-2-BX.
Below set forth the connection and the function of each major part one by one:
Fixedly braces 7 and clamping band 8 between slide rail 11 and health, are used for connecting and fixedly health and slide rail 11.
Electronic slide rail device 16: be in slide rail 11 and main looking between the Ji 6, function has two: slide on slide rail 11 (1), adjusts host wing 6 in the residing position of health, to reach the purpose of adjusting center of gravity; (2) it can make host wing 6 change angle among a small circle, be used for aircraft vertical takeoff and landing and conventional putting down when flying the two condition transition, change driving engine to people and aircraft force direction, concrete operations lift by take off vertically to routine flat fly over to cross illustrate, the aviator holds bar handle 1, draw control arm 4 to the health direction downwards, because the point or the pointed end of circular arc of electronic slide rail device 16, be positioned at the spill guide groove 2 on host wing 6 aerofoils, the tractive control arm makes host wing 6 aerofoils turn an angle to horizontal direction, and driving engine is given the power before aircraft person and tendency of aircraft, cooperate other actions again, realize taking off vertically and cross to flat the flying over of routine.
Host wing 6: host wing 6 links to each other with automatically controlled slide rail device 16, on it with its line of centers for being symmetrically arranged with two driving engines 5, host wing 6 is to cooperate driving engine 5 to share the important means of human body weight awing, aloft fuel oil all is stored in wherein.
Driving engine 5: combine with host wing 6, enough power is provided for aviator and aircraft, enough thrust-weight ratios need be arranged, can select airscrew engine for use---a kind of very ripe driving engine, safety is very good but under power can be selected jet engine for use---ripe driving engine, safety is general, but power is very desirable, comparatively is fit to native system, also can select the rocket type driving engine for use---can select for use in test.
Vertical fin 9: combine with the end of slide rail 11, play a part stable awing.
Control arm 4: control arm 4 one ends link to each other with host wing 6, the other end is a bar handle 1, it is to be used for the angle of the main control system wing 6 and escape, the angle of the main control system wing 6 was set forth in electronic slide rail device 16 parts: the control escape is like this, aviator's both arms are outwards broken control arm 4 into two with one's hands, control arm 4 drives pipe link and affects bar 23 outside tractives, pipe link affects bar 23 to drive pipe link and affects steel wire 22, and then outwards extract pipe link 13, pipe link 13 1 and extracting, host wing 6 and driving engine 5 promptly unload, and parachute is opened subsequently, thereby make aviator's safe escape.
Bar handle 1: combine with control arm 4, handle with hand, it can finish the work of control oil supply speed governing.
Empennage 10: link together with people's shank, shared the following part weight of center of gravity, cooperated host wing 6 effectively, it also can adjust aloft attitude, utilizes the turning in aviator's knee joint and hip joint to finish above work.
The present invention is manned free flight technology of a kind of brand new and brand new vertical takeoff and landing technology, at first, it can finish the dream of the same free flight of portrait bird, it is the design of a human flight the most suitable, secondly as a kind of up-to-date technology of vertical takeoff and landing (VTOL), the vertical takeoff and landing that also can be applied to other flying body designs.
The present invention is done following the elaboration with the meaning that produces:
1, it can make the people freely circle in the air on high, and it has finished the dream of human free flights for thousands of years Think.
2, owing to its maneuverability, from then on it may change the structure of future war, particularly for army Some rapid response forces of team, because its price is low, mobility, easy operating and distinctive performance, it Appearance never inferior to the appearance of tank.
3, at military aspect gradually after the maturation, can be gradually to the development of product for civilian use aspect, because technology is Can not forever maintain secrecy, its development potentiality aspect the commercial market also is very huge in addition, and it can Be applied to all trades and professions, it may be to the impact of the trip generation matter in future.
This is novel applied widely: such as naval, ground force, air force, marine corps, Armed Police Force, sea Each applications such as upper police, extra large land police, traffic, geology, aerial sports, agricultural, animal husbandry.
Select Fig. 4 as Figure of abstract.
Claims (2)
1, a kind of manned aerobat capable of landing or taking-off vertically is characterized in that it comprises fixedly braces (7), clamping band (8), slide rail (11), electronic slide rail device (16), host wing (6), driving engine (5), control arm (4), bar handle (1), empennage major parts such as (10);
Wherein fixedly braces (7) is two, be separately fixed on the slide rail (11), the aviator back of the body carry two fixedly braces (7) slide rail (11) carried on the back put at back, on slide rail (11), also be provided with plurality of fixed band (8), slide rail (11) firmly is strapped on one's body the aviator, host wing (6) links to each other with slide rail (11) by electronic slide rail device (16), the aerofoil of host wing (6) is parallel to aviator's health plane, host wing (6) is gone up line of centers with host wing (6) for being symmetrically arranged with two driving engines (5), the fuel oil of flight usefulness is stored in the host wing (6), be provided with two control arms (4) at the top of host wing (6), the other end of two control arms (4) all is positioned at the aviator front, and this end is equipped with bar handle (1), each fixes an empennage (10) at aviator's shank place, empennage (10) aerofoil and aviator's health plane parallel;
Slide rail (11), electronic slide rail device (16), connection between the wing (6): electronic slide rail device (16) one ends embed in the slide rail (11), this end of electronic slide rail device (16) is provided with some pulleys (19), one group of pulley (19) is positioned on the external slideway (24) of slide rail (11), another group pulley (19) is positioned on the inner slide (25) of slide rail (11), be provided with synchronous dynamo (14) in the electronic slide rail device (16), synchronous dynamo (14) driven gear group (15), thereby drive one and change line wheel (17), also be provided with one and change line wheel (17), pulley affects steel wire (18) one ends to be fixed on an end of slide rail (11), the other end becomes the figure of eight to walk around two changes line wheel (17), be fixed on slide rail (11) other end then, the other end of electronic slide rail device (16) becomes point or circular arc pointed, be positioned at the spill guide groove (12) on host wing (6) aerofoil, and link to each other with host wing (6) with pipe link (13), pipe link (13) is positioned at the groove (26) of host wing (6), also be provided with spring (21) in the groove, spring (21) one ends link to each other with pipe link (13), the other end is connected in pipe link far away (13) one ends of groove (26), the end that pipe link (13) links to each other with spring (21) also is connected with pipe link and affects steel wire (22), affect the other end of steel wire (22) to pull out outside the host wing (6), affect bar (23) to link to each other with pipe link, pipe link affects bar (23) and control arm (4) to be fixed together;
Control part adopts reversible PWM amplifirer speed system, from+V,-V holds a given incoming signal and the feedback speed signal addition that records through tachogenerator to send into 1 end of preamplifier K1, the 2 end ground connection of K1, the speed signal that records through tachogenerator feeds back to the corrective loop simultaneously, 1 end that the signal plus of signal after the correction and the output of K1 mouth is sent into K2 amplifies once more, proofread and correct output simultaneously, the 2 end ground connection of K2, the amplifying signal of K2 mouth output inserts 2 ends of comparator A, the signal that triangular-wave generator produces inserts 1 end of comparator A, the triangular signal addition that the amplifying signal of K2 output and triangular-wave generator produce produces modulated pulse signal to the circuit in logical delay through comparator A, and logical delay, circuit was divided into four tunnel logic control impulse singlas with modulating pulse: logical delay, circuit output end 1 was to EVK31-050
1-1-AX, logical delay, circuit 3 was to EVK31-050
1-3-AY, logical delay, circuit output end 4 was to EVK31-051
2-4-BY, logical delay, circuit output end 2 was to EVK31-050
2-2-BX.
2, VTOL craft according to claim 1 is characterized in that being provided with two vertical fins (9) at the end of slide rail (11), and is angled with aviator's health plane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 97112823 CN1203167A (en) | 1997-06-24 | 1997-06-24 | Manned aerobat capable of landing or taking-off vertically |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 97112823 CN1203167A (en) | 1997-06-24 | 1997-06-24 | Manned aerobat capable of landing or taking-off vertically |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1203167A true CN1203167A (en) | 1998-12-30 |
Family
ID=5172489
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 97112823 Pending CN1203167A (en) | 1997-06-24 | 1997-06-24 | Manned aerobat capable of landing or taking-off vertically |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1203167A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102076561A (en) * | 2008-06-27 | 2011-05-25 | 马丁飞机有限公司 | Personal flight vehicle including control system |
| CN102730192A (en) * | 2011-04-14 | 2012-10-17 | 戴瑾 | Vertical take-off and landing aircraft |
| CN104843184A (en) * | 2015-04-14 | 2015-08-19 | 王学礼 | Personal air vehicle |
| CN107010219A (en) * | 2017-04-18 | 2017-08-04 | 佛山市神风航空科技有限公司 | A kind of walk help knapsack and its walk help mode |
| CN108791756A (en) * | 2017-04-29 | 2018-11-13 | 徐曙辉 | Portable pressure spraying machine |
| CN112429222A (en) * | 2020-12-03 | 2021-03-02 | 北方工业大学 | Single-person wing type jet backpack aircraft |
| CN113548180A (en) * | 2021-08-04 | 2021-10-26 | 郑桂良 | Novel single aircraft |
| WO2022257806A1 (en) * | 2021-06-10 | 2022-12-15 | 米建军 | Back-borne aircraft |
-
1997
- 1997-06-24 CN CN 97112823 patent/CN1203167A/en active Pending
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102076561A (en) * | 2008-06-27 | 2011-05-25 | 马丁飞机有限公司 | Personal flight vehicle including control system |
| CN102730192A (en) * | 2011-04-14 | 2012-10-17 | 戴瑾 | Vertical take-off and landing aircraft |
| CN104843184A (en) * | 2015-04-14 | 2015-08-19 | 王学礼 | Personal air vehicle |
| CN107010219A (en) * | 2017-04-18 | 2017-08-04 | 佛山市神风航空科技有限公司 | A kind of walk help knapsack and its walk help mode |
| CN108791756A (en) * | 2017-04-29 | 2018-11-13 | 徐曙辉 | Portable pressure spraying machine |
| CN108791756B (en) * | 2017-04-29 | 2023-09-29 | 徐曙辉 | Portable pressure spraying machine |
| CN112429222A (en) * | 2020-12-03 | 2021-03-02 | 北方工业大学 | Single-person wing type jet backpack aircraft |
| WO2022257806A1 (en) * | 2021-06-10 | 2022-12-15 | 米建军 | Back-borne aircraft |
| CN113548180A (en) * | 2021-08-04 | 2021-10-26 | 郑桂良 | Novel single aircraft |
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