CN101628156A - High-rise life saving device - Google Patents
High-rise life saving device Download PDFInfo
- Publication number
- CN101628156A CN101628156A CN200810023125A CN200810023125A CN101628156A CN 101628156 A CN101628156 A CN 101628156A CN 200810023125 A CN200810023125 A CN 200810023125A CN 200810023125 A CN200810023125 A CN 200810023125A CN 101628156 A CN101628156 A CN 101628156A
- Authority
- CN
- China
- Prior art keywords
- air
- main wing
- angle
- wing
- flow
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Landscapes
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a high-rise life saving device. A nozzle of a compressed air tank jets high-speed airflow to wings, and then the upper and lower surfaces of the wings produce a pressure difference so as to produce a lift force; and the magnitude of the lift force is changed by adjusting the flow of the nozzle, the advancing direction of an aircraft is changed by adjusting angles of a vertical empennage, and an auxiliary nozzle is increased for emergently changing the direction.
Description
Affiliated field: aircraft class
Background knowledge: existing aircraft comprises airborne vehicle, spacecraft and rocket, guided missile.Airborne vehicle comprises aerodone, fire balloon, airship, aircraft, helicopter etc., the invention belongs to the airborne vehicle class, but is different from above-mentioned several aircraft.
Summary of the invention:
Common aircraft or helicopter, all be to make wing with respect to air movement, rely on wing top and bottom pressure differential to produce lift, the air of wing of the present invention and surrounding environment does not do relative motion, but rely on the nozzle of compressed air cylinder to spray high velocity air to wing, make the wing top and bottom produce pressure differential, thereby generation lift, and the speed of passing through the adjusting air-flow changes the size of lift, regulate the angle of vertical tail and come the direction of advance of change of flight device, and add a pilot jet and be used for promptly changing direction.Puffer under the seat and air pump belong to and select piece installing, can significantly increase the stroke of aircraft after loading onto.
Description of drawings:
Fig. 1 is monnolithic case figure.Wherein 1 is the main jet pipe, and 2 is main wing, and 3 is vertical tail, and 4 is support.1 and 2 are fixed on 4, and the angle of attack of main wing and horizontal plane can be adjusted when not taking off, and is fixed when taking off.5 is gascollecting cap cylinder, also is fixed on the support 4, and 6 for adjusting jet pipe and control valve, and purpose is the speed that control is advanced.7 is main jet pipe control valve, in order to the speed of adjustment air-flow, thus the size of change lift.8 is seat, and support 4 and 8 is connected as a single entity, and 9 is the combination of engine and air pump, for selecting piece installing, selects for use, can increase the stroke of aircraft greatly, but also increases cost, and makes complete machine structure more complicated.10 for emergent jet pipe when preventing to run into barrier in-flight, emergency turn usefulness.11 is air gauge, and 12 is the vertical tail guiding mechanism, connects with connecting rod between two empennages, form quadric chain with main wing, the empennage side is connected with pedal with brake cable, and the pedal opposite side catches on extension spring, the left-hand tread plate brake cable is preceding, extension spring after, right-hand tread plate is with it.
Embodiment: each part on deck after, earlier support and seat are linked together with bolt, rack-mount main wing again, then empennage, gas receiver, main jet pipe, adjust jet pipe, each control valve, meet an urgent need jet pipe, pipeline etc. are rack-mount.If select mounted engine and air pump, again engine is connected with seat with air pump.After treating complete machine assembling, gascollecting cap cylinder is inflated, reached rated pressure, take a flight test, the angle of attack of adjusting main wing reaches best, and fixes this angle and get final product.
Claims (4)
1, a kind of high-rise escape apparatus, it is characterized in that relying on the nozzle of compressed air cylinder to spray high velocity air to fixing wing, make the wing top and bottom produce pressure differential, thereby generation lift, and the speed of passing through the adjusting air-flow changes the size of lift, regulate the angle of vertical tail and come the direction of advance of change of flight device, and add pilot jet and be used for promptly changing direction.
2, according to the described high-rise escape apparatus of claim one, its feature comprises that a cover high pressure tank and air-flow spray and control system, and several high pressure tanks are cascaded, and are the nozzle air feed jointly, also are convenient to inflation simultaneously.Adopt the flow of throttle valve control air-flow, to regulate the lift size.
3, according to the described high-rise escape apparatus of claim one, its feature comprises the main wing that is fixed on the support and the vertical tail hinged with main wing, there is the angle of about 15 degree to regulate between main wing and support, must be fixing after regulating, prevent that the variation of main wing angle causes flying out of control in-flight.The main wing of this mode is to be simplified control system.Empennage and main wing are hinged, can rely on the angle control system to do the adjustment of angle in vertical direction, with the change of flight direction.
4, according to the described high-rise escape apparatus of claim one, its feature comprises the engine and the air pump combination of a cover choosing dress, and air pump continues to provide gases at high pressure to gascollecting cap cylinder, thereby prolongs the hang time, increases stroke.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200810023125A CN101628156A (en) | 2008-07-14 | 2008-07-14 | High-rise life saving device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200810023125A CN101628156A (en) | 2008-07-14 | 2008-07-14 | High-rise life saving device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101628156A true CN101628156A (en) | 2010-01-20 |
Family
ID=41573541
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200810023125A Pending CN101628156A (en) | 2008-07-14 | 2008-07-14 | High-rise life saving device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101628156A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103083830A (en) * | 2013-01-07 | 2013-05-08 | 南京航空航天大学 | Rotary wing type high-rise life-saving equipment |
| CN105197242A (en) * | 2015-10-13 | 2015-12-30 | 苏州福泽能源科技有限公司 | Emergency landing vehicle |
| CN105194811A (en) * | 2015-11-16 | 2015-12-30 | 唐哲敏 | High-rise escape equipment |
| CN105664382A (en) * | 2016-03-10 | 2016-06-15 | 四川福莱特科技有限公司 | Anti-collision rotor wing type high-rise life saving equipment and damper used by same |
-
2008
- 2008-07-14 CN CN200810023125A patent/CN101628156A/en active Pending
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103083830A (en) * | 2013-01-07 | 2013-05-08 | 南京航空航天大学 | Rotary wing type high-rise life-saving equipment |
| CN103083830B (en) * | 2013-01-07 | 2014-05-07 | 南京航空航天大学 | Rotary wing type high-rise life-saving equipment |
| CN105197242A (en) * | 2015-10-13 | 2015-12-30 | 苏州福泽能源科技有限公司 | Emergency landing vehicle |
| CN105194811A (en) * | 2015-11-16 | 2015-12-30 | 唐哲敏 | High-rise escape equipment |
| CN105664382A (en) * | 2016-03-10 | 2016-06-15 | 四川福莱特科技有限公司 | Anti-collision rotor wing type high-rise life saving equipment and damper used by same |
| CN105664382B (en) * | 2016-03-10 | 2018-09-14 | 四川福莱特科技有限公司 | A kind of anticollision rotary wind type high-rise building life saving equipment and its damper used |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111158387B (en) | Aircraft three-axis attitude control system and method based on active flow control | |
| US9884686B2 (en) | Aircraft including an engine attachment with a control surface | |
| US9180974B2 (en) | Aircraft with an integral aerodynamic configuration | |
| US10099793B2 (en) | Distributed electric ducted fan wing | |
| CA2770740C (en) | Systems and methods for attenuation of noise and wakes produced by aircraft | |
| US20190168861A1 (en) | Under the wing-mounted jet engine with pivotal swivel joint to produce directional thrust vectoring thru swivel angle | |
| US8152109B2 (en) | Method and system for controlling fluid flow in relation to a foil and harnessing energy therefrom | |
| CN101052565A (en) | High-lift distributed active flow control system and method | |
| WO2005065071A2 (en) | Supersonic aircraft | |
| CN111776199B (en) | Turbojet air supply system for jet flight control technology | |
| CN103201172A (en) | Aircraft with wings and a system for minimizing the influence of unsteady flow states | |
| WO2008042162A3 (en) | Air-vehicle augmented kinesthetic control system | |
| CN103359281A (en) | Surface element for aircraft, aircraft and method for improving high-lift generation on a surface element | |
| CN109502037B (en) | Water surface forced landing mechanism of reverse air-jet ventilation cavitation aviation aircraft | |
| CN101628156A (en) | High-rise life saving device | |
| CN104787306A (en) | Low-speed safety aircraft capable of controlling flight attitude by aerodynamic force | |
| CN104477376A (en) | Combined pneumatic control method for aerodynamic rudder/reaction control system of hypersonic flight vehicle | |
| CN100422044C (en) | Solar energy buoyancy force controllable, self control balance helium gas aircraft | |
| CN103612746A (en) | Fairing structure of suspension in wing suspension layout aircraft | |
| WO2017121116A1 (en) | Engine for vertically taking off or landing with airfoil lift | |
| EP1574426A1 (en) | Method for producing a lifting force, aeroplane, take off and landing method | |
| CN208715466U (en) | Unmanned aerial vehicle (UAV) control device and unmanned plane based on flow field control | |
| RU2385260C1 (en) | Aircraft wing | |
| US3012738A (en) | Air-borne vehicle | |
| RU2466061C2 (en) | Flight vehicle (versions), flight vehicles parts, method of exploiting flight vehicle and its parts |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Open date: 20100120 |