CN100387488C - Method for supporting a propelled flying object during take-off and/or landing - Google Patents
Method for supporting a propelled flying object during take-off and/or landing Download PDFInfo
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- CN100387488C CN100387488C CNB2004800157765A CN200480015776A CN100387488C CN 100387488 C CN100387488 C CN 100387488C CN B2004800157765 A CNB2004800157765 A CN B2004800157765A CN 200480015776 A CN200480015776 A CN 200480015776A CN 100387488 C CN100387488 C CN 100387488C
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- flow
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Abstract
The invention relates to a method for supporting a propelled flying object during take-off and/or landing. Support is given by means of a fluidic current, which is generated at a fixed point in relation to a take-off or landing surface (10) and which transfers energy to the flying object. The invention also relates to a device comprising a fluidic current generator (11) for producing said fluidic current.
Description
Technical field
The present invention relates to a kind of aircraft lands of dynamic device and/or method and apparatus that takes off supported.
Background technology
Here aircraft is meant any object that is fit to by self engine installation motion not in contact with the ground in the atmospheric envelope of planet, for example aircraft.
No matter take-off process and landing mission structurally still all mean a kind of special challenge in the use for this aircraft.
Usually the take-off and landing runway that need grow for the take-off and landing of aircraft.But the take-off and landing runway of preparation length is time-consuming and with high costs.Add not is to provide enough positions to be used for regular take-off and landing runway anywhere.This situation especially occurs on the carrier-borne landing facility, and can bring problem too in other occasions, for example in the area on many mountains.May on short runway, support landing mission by capturing rope here, require to go home especially accurately (vector) for this reason.This method means the high training expenses to the aircrew.
Summary of the invention
The purpose of this invention is to provide a kind of method and a kind of equipment, they support the taking off and/or landing mission of aircraft of (assistance) dynamic device especially simply.
For this reason, the invention provides a kind of aircraft lands of dynamic device and/or method of taking off supported, wherein, the method comprises provides a kind of with respect to a landing or the district's fluid stream that is used for applying to aircraft energy of generation regularly that takes off, and it is characterized by: the density of fluid stream is adjusted as the case may be.
According to said method, provide a kind of with respect to a landing or the district's fluid stream that is used for applying energy of generation regularly that takes off to the capable device of chi.
The present invention also provides a kind of aircraft lands of dynamic device and/or equipment that takes off supported, comprise at least one fixing fluid flow-generator in district that lands or take off with respect to one, it is designed to provide a kind of fluid stream, be used for applying energy to aircraft, it is characterized by: in addition the fluid flow-generator also is designed for the density that institute's fluid that provides flows is provided.
Equipment of the present invention has at least one fixing fluid flow-generator in district that lands or take off with respect to one, and producer is designed to provide a kind of fluid stream that is used for applying to aircraft energy.
The present invention is based on this thought, that is, even without the auxiliary device that uses machinery, aircraft is that the energy that is used for the plus or minus acceleration/accel that takes off or land is also not necessarily only supplied with by aircraft.Exactly, a kind of fluid stream of aiming at aircraft can be supported the braking or the acceleration of aircraft.
An advantage of the invention is that it can generally and neatly use.The present invention can realize the support to aircraft takeoff and landing of easy operating under the situation that need not long take-off and landing runway.Additional benefit of the present invention is, the present invention can with the type in landing site, with weather condition and irrelevant with the type of aircraft.Can realize economically and at short notice in a simple manner by system of the present invention in this case.
It takes off and/or lands, and also can to design than so far by the supported aircraft of the present invention simpler, because they can take off and/or land definitely independently again.If the parts that no longer need some to be used in landing, for example wheel is then done like this and has also been improved safety, because the fault neurological susceptibility of these parts recedes into the background.
By a favourable design of the present invention, the direction of fluid stream can be adjusted as the case may be.Here, direction also comprises with respect to taking off and/or the angle of footprint.Particular case can for example be determined by the direction of going home, aircraft height and/or distance.If use a plurality of independent fluid streams, then their direction can advantageously be adjusted separately.
By another favourable design of the present invention, at least one physical parameter of fluid stream can be adjusted as the case may be.A kind of so here physical parameter can for example be the temperature of fluid stream, the density of fluid stream, the speed of fluid stream, the homogenieity of fluid stream or the laminar flow share of fluid stream.It is definite that wherein particular case can for example be passed through ambient temperature, aircraft speed, type of aircraft, aircraft distance etc.
The adjustment of temperature can be undertaken by heater element and/or cooling element.Fog can be for example avoided with the temperature that flows than higher fluid, or also the aircraft icing can be avoided or prevent.The temperature that reduces fluid stream can for example prevent that aircraft is overheated.
If the fluid stream that provides has the unit intensity of regulation, and pass through it, then can improve the effect of fluid stream, that is strengthen its brake action or its accelerating action with the higher material enrichment of at least a unit intensity.
Can when the fluid stream innate need of the economy that provides, add a kind of fire extinguishing agent equally, for example fly near carry-on catching fire in order to put out.
The fluid stream that provides can for example be by the artificial wind of existing atmosphere, a kind of flow of material or a kind of streams.The fluid flow-generator that is used for producing fluid stream can be a kind of at the known fluid flow-generator of real work, and blowing engine for example is such as the turbofan that is used in aircraft traditionally (Mantelstromtriebwerk).If use existing already present fluid flow-generator, then can especially promptly realize by system of the present invention.
In order to support aircraft lands, at first provide a kind of fluid stream that is applicable to the braking aircraft by a kind of form of implementation of the present invention.Then, the fluid Flow Control is made as aircraft is dropped on the touch-down zone from suspended state.
In order to support aircraft takeoff, at first provide a kind of fluid stream that makes aircraft be elevated to suspended state from the district of taking off that is applicable to by a kind of form of implementation of the present invention.A kind of fluid stream that aircraft is quickened towards the direction of expectation that is applicable to then is provided.
In order to support taking off of aircraft, by the another kind of form of implementation of the present invention, aircraft at first quickens voluntarily by traditional mode.But this self take off, that is from raked floor then obtains by method of the present invention or by equipment support of the present invention and thereby be accelerated.By corresponding mode, the aircraft of Zhe Luing can be soon by braking by method of the present invention or by the support of equipment of the present invention behind the contact landing runway in a conventional manner.Therefore do not need long taking off or landing runway, but only need one section weak point for quickening required distance.According to type of airplane, this distance can be 50 to 100m.The advantage of this design plan is that it is applicable to transforms existing take-off and landing runway.
Advantageously, all couplings of fluid stream are determined automatically by a regulating control and are adjusted.
(meaning is: any part of object does not all contact with ground to be used to support to be adapted at the endoatmosphere motion not in contact with the ground of planet.The layer of at least one molecular thickness of atmosphere is between this object and the ground) object (=aircraft, aircraft) take off or the method and/or the equipment of landing mission are characterised in that, this object quickens (define by physics and be meant positive acceleration and negative acceleration) here in all in check air flow of all physical parameters (temperature, density, speed, homogenieity, laminarity) (=wind, flow of material, streams) that for example blowing engine that also can turn round in case of necessity He can install movably along direction in space by brute force produces, and thereby takes off or land.In order to improve the effect of acceleration/accel, air flow can be by strengthening with the higher material enrichment of unit intensity (for example can spray water droplet, also it is contemplated that other enrichment materials, as long as they can reach this purpose).
According to said method and/or a design of equipment at landing mission, can for example be envisioned for and allow aircraft fly in a kind of flow of material that there is no need to control, it is added the propelling energy of aircraft aircraft is reduced to zero with respect to ground-surface speed by its kinetic energy, and, make aircraft because the lifting body of the aircraft that becomes a mandarin has the required lift that suspends by the intrinsic speed of flow of material.(other relevant details can be consulted any physical textbook.) by the turning to, reduce or common control (refer to change all geometric parameters (x, y, z, angle) here and change physical parameter) of flow of material and aircraft power, aircraft is landed.
Also can be used in take-off process now with a kind of method and/or equipment by opposite mode.For example take-off process can be imagined the cable traction that is similar to aerodone and takes off, by the analogy method reasoning, will finishing in conjunction with the coiling rope of task is aircraft to be quickened and the generation wind surface, and here this task is born by the engine installation of a rotatable blowing engine of fixed type and aircraft.Also be limited to this example here, resemble under the situation of landing mission, also only done very briefly bright because the method for taking off especially thinks relevant with the type of aircraft.
However still represented another kind of preferred design, because it has embodied one of varied possibility, it can be realized rapidly and be the most receptible scheme.By this design, method/equipment that part has illustrated above having used: aircraft at first quickens as usually, and new mode by introduction here and/or equipment are finally finished and taken off before the process of routine finishes then.This change is interesting in the transition period of transforming existing airport, because these airports are unworthy considering that existing airstrip of reorganization and expansion and manager do not wish to transform fully yet (is interested at present in AIRBUS-mid-air-bus airport, reorganization and expansion hamburger! )
Preferably design by another of method and/or equipment,, for example avoid or cancel fog or aircraft icing in the workspace areas by the temperature of control flow of material, or reduce overheated.
By another kind of form of implementation, can also be in flow of material especially selectivity on purpose add fire extinguishing agent, for example fire foam.
By another kind of preferred form of implementation, all control process automations are also passed through common for example computer based regulating control and are implemented.
For the example of another visualization is provided, can here quote from the fountain or the ball that in air-flow, jumps.Similarly and add all the situation differences that can expect and possible terms of settlement, for example the laminarity or the homogenieity of related substance stream have designed a kind of preferred form of implementation.By another kind of preferred form of implementation, utilize large-scale turbofan as blowing engine, as employed turbofan in civil aviation.
Above-mentioned all measures all cause realizing described method and/or equipment (several months development time only in the shortest time! ).
Being used to of here being introduced supports the method for aircraft takeoff or landing mission and/or equipment can be used in land landing or carrier-borne landing, and irrelevant fully with weather condition.Equally also irrelevant with the design of aircraft.
In diversified advantage, except that touching upon above, also should list other outstanding advantages:
The training expenses that the aircrew is lower: expect for this reason needing target approach exactly in order to land by capturing this inexpressible method of rope.Equally, take-off process also wants much simple
Cost saving and time!
The modular construction mode: the device of using with the land landing on the warship can be designed as consistent.
Greatest possible flexibility and manoevreability: do not need to take off or landing runway, only need be used for the space (difference according to flight is shorter than 50m to 100m) of accelerator necessity, that is to say and cancelled the necessary logistics support of this part.Almost completely save and for example build military airfield
Cost saving and time!
Structural complexity when reducing aircraft manufacturing, that is more useful loads are arranged.Therefore no longer need to be designed for the omniplane of supersonic flight.Less physical activities part=higher (technology) safety.Consequently: less senior specialized personnel and minimizing technical failure.
Description of drawings
Describe design of the present invention referring to accompanying drawing in detail by embodiment.Wherein:
Fig. 1 schematically illustrates the conduct of take-off and landing device by apparatus embodiments of the present invention; And
Fig. 2 illustrates the diagram of circuit of take-off and landing device shown in Figure 1 work.
The specific embodiment
Fig. 1 schematically illustrates a kind of take-off and landing device of taking off and landing by support of the present invention.Here aircraft can be a kind of aircraft of traditional type.
The take-off and landing device has the take-off and landing district 10 of a circle.10 by eight large-scale turbofan 11 of uniform spacing installation around the take-off and landing district.Every turbofan 11 is rotatably mounted and has temperature to adjust element.Temperature is adjusted element and is comprised a graticule mesh shape plug-in unit 12 in turbofan 11 air discharge port districts separately, and wherein, the temperature of graticule mesh shape plug-in unit 12 is adjustable.Set a spraying equipment 13 for every turbofan 11 in addition, it can spray water droplet in the air discharge port district of turbofan 11.
In addition, the take-off and landing device has a regulating control 14 based on computing machine.Regulating control 14 is connected with receiving device 15 with detection.The latter comprises temperature sensor and is used to receive by the receptor that flies the signal that near aircraft sends.Regulating control 14 also has a control channel to go to every turbofan 11 and goes to each spraying equipment 13.For the purpose of view was clear, described passage only represented to be used for wherein a turbofan 11 and one of them spraying equipment 13 as an example.
The mode of operation of the take-off and landing device of the flowcharting Fig. 1 among Fig. 2.
If aircraft is in the state of going home that will land, then regulating control 14 is at first determined the direction that aircraft is sudden.This for example can be undertaken by coordinate setting, and coordinate setting is sent by the receptor of aircraft to detection and receiving device 15.By another kind of scheme or additionally, the determining of the direction of going home also can be undertaken by the ground detection of flight parameter.Regulating control 14 is by the control signal adjustment, and the air-flow that will produce is head-on aimed at aircraft.
In addition, information of some relevant aircrafts itself of flight transmission, for example about its speed, highly, weight and shape, these information are by detecting and the receptor reception of receiving device 15.Regulating control 14 serves as that the basis determines that the air-flow that will produce is used for the required speed of aircraft braking with these information.Speed is adjusted turbofan 11 by control signal more accurately, makes by the kinergety of Combined toy plane engine installation energy and contrary this function of air-flow the speed of aircraft to be reduced to zero.If desired, can also further strengthen the validity of air-flow here, promptly the control signal command injection equipment by regulating control 14 sprays into water droplet in the air-flow that will produce for this reason, to improve the density of air-flow.Control signal command injection equipment 13 that when needed can also be by regulating control 14 sprays into a kind of fire extinguishing agent in the air-flow that will produce.
Determining of the required speed of air-flow that obviously, produce also can be by the available scheme of another kind or additionally undertaken by the ground detection of flight parameter.
In addition, the temperature sensor of detection and receiving device 15 is determined ambient temperature.When ambient temperature was low especially, regulating control 14 was adjusted the graticule mesh 12 of element by control signal instruction heating-up temperature on turbofan 11, to prevent because the water droplet that sprays in the air-flow causes icing, or in order to remove the icing that exists on the aircraft.When ambient temperature was high especially, regulating control 14 is by the graticule mesh 12 of control signal instruction chilling temperature adjustment element on turbofan 12, and was overheated to prevent aircraft.
Turbofan 11 might fly in this air-flow at the air-flow and the aircraft that provide parameter through adjusting under the support of spraying equipment 13 now.Make aircraft braking thus and above take-off and landing district 10, place suspended state.For this purpose, the direction of turbofan 11 air-flows and other parameters should be collaborative each other with aircraft by regulating control 14 control corresponding.
If aircraft has been in this position, controller 14 impels turbofan 11 to reduce the speed of the air-flow that will produce by control signal corresponding, thereby makes aircraft landing to ground.By another kind of scheme or additionally, for being descended, aircraft also can change other parameters of the air-flow that will produce by the control signal of regulating control 14, and for example change by spraying equipment 13 and spray into the water yield in the air-flow.
Taking off of aircraft by supported at the illustrated opposite order of aircraft landing.
In order to take off, aircraft at first is positioned in the takeoff setting between the turbofan 11.Regulating control 14 is implemented predetermined takeoff procedure now, and in view of the above, turbofan 11 at first produces and provide air-flow, and it places aircraft the suspended state of take-off and landing runway top.From then on state sets out, and aircraft is by the engine installation of oneself and additionally by the air-flow that is provided by turbofan 11 suitable orientation and intensity acceleration.Here the direction of air-flow depends on the course of aircraft plan.
By another kind of scheme, also can use several turbofan 11, to cause an air-flow with reverse its intensity increase of aircraft.Meanwhile utilize the power of aircraft self, so that aircraft is with respect to quickening in face of its airflow flowing.Here the intensity of air-flow and self power are coordinated with each other, and aircraft is moved from its initial position as few as possible.If reach enough relative accelerations, then aircraft can rise from the district 10 of taking off as traditional take-off process.This design plan can significantly shorten, the needed takeoff runway of aircraft that takes off by self power.
Air-flow is as being adjusted into desired temperatures by temperature adjustment element by control signal by regulating control 14 the landing mission on turbofan 11.In addition, but for the effect regulating control 14 that strengthens air-flow still command injection equipment 13 water droplet is sprayed in the air-flow of generation.
Illustrated form of implementation just expression from by method of the present invention with by a kind of selection the many possible forms of implementation of equipment of the present invention.
Claims (21)
1. support the aircraft lands of dynamic device and/or the method for taking off, wherein, the method comprises that providing a kind of lands or fluid that the district (10) of taking off produces regularly is used for applying to aircraft energy flows with respect to one, and it is characterized by: the density that fluid flows is adjusted as the case may be.
2. in accordance with the method for claim 1, it is characterized by, the direction of fluid stream is adjusted as the case may be.
3. in accordance with the method for claim 1, it is characterized by, the value of other at least one physical parameter of fluid stream is adjusted as the case may be.
4. in accordance with the method for claim 3, it is characterized by, described at least one physical parameter comprises one of following parameters at least: the laminar flow share of the speed of the temperature of fluid stream, fluid stream, the homogenieity of fluid stream and fluid stream.
5. in accordance with the method for claim 1, it is characterized by, the fluid stream that is provided has the unit intensity of regulation, and when needed by the higher material enrichment of at least a unit intensity.
6. in accordance with the method for claim 1, it is characterized by, in the fluid stream that provides, add a kind of fire extinguishing agent.
7. in accordance with the method for claim 1, it is characterized by, the fluid stream that is provided is a kind of by the artificial wind of existing atmosphere, a kind of flow of material or a kind of streams.
8. in accordance with the method for claim 1, it is characterized by,, at first provide a kind of fluid stream that is applicable to the braking aircraft in order to support aircraft lands, and, a kind of fluid stream that makes aircraft drop to touch-down zone (10) from suspended state that is applicable to is provided then.
9. in accordance with the method for claim 1, it is characterized by,, at first provide a kind of fluid stream that makes aircraft upwards place suspended state from the district (10) of taking off that is applicable in order to support aircraft takeoff, and, a kind of fluid stream that aircraft is quickened towards the direction of expectation that is applicable to is provided then.
10. support the aircraft lands of dynamic device and/or the equipment that takes off, comprise at least one fixing fluid flow-generator (11) in district (10) that lands or take off with respect to one, it is designed to provide a kind of fluid stream, be used for applying energy to aircraft, it is characterized by: in addition the fluid flow-generator also is designed for the density that institute's fluid that provides flows is provided.
11. according to the described equipment of claim 10, it is characterized by, can be directed by the fluid stream that fluid flow-generator (11) provides.
12. according to the described equipment of claim 10, it is characterized by, the fluid flow-generator is designed for the value that other at least one physical parameter that institute's fluid that provides flows is provided.
13. according to the described equipment of claim 10, it is characterized in that, be provided with a heater element (12) that is used to heat the fluid stream that is provided.
14. according to the described equipment of claim 10, it is characterized in that, be provided with a cooling element (12) that is used to cool off the fluid stream that is provided.
15. according to the described equipment of claim 10, it is characterized in that, be provided with one and be used for an interior material feeding device (13) of fluid stream that provides is provided a kind of additional material, wherein, a kind of higher unit intensity of fluid stream that is provided that compares is provided additional material.
16. according to the described equipment of claim 10, it is characterized in that, be provided with one and be used for the interior fire extinguishing agent feedway (13) of fluid stream that is provided is provided fire extinguishing agent.
17. according to the described equipment of claim 10, it is characterized by, described at least one fluid flow-generator comprises at least one blowing engine (11).
18. according to the described equipment of claim 17, it is characterized by, described at least one blowing engine comprises at least one turbofan (11).
19. according to the described equipment of claim 10, it is characterized by: described at least one fluid flow-generator (11) is designed to, and provides a kind of by the artificial wind of existing atmosphere, a kind of flow of material or a kind of streams as fluid stream.
20., it is characterized in that according to the described equipment of claim 10, be provided with a regulating control (14), be used for determining the fluid stream that provides by described at least one fluid flow-generator at least one parameter optimum value and be used to adjust this at least one parameter value.
21. according to the described equipment of claim 20, it is characterized by: described at least one parameter comprises one of following parameters at least: the speed of the temperature of the direction of fluid stream, fluid stream, the density of fluid stream, fluid stream, the homogenieity of fluid stream and the laminar flow share of fluid stream.
Applications Claiming Priority (4)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE10326144 | 2003-06-06 | ||
| DE10326144.3 | 2003-06-06 | ||
| DE10327743.9 | 2003-06-18 | ||
| DE10328292.0 | 2003-06-23 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1802287A CN1802287A (en) | 2006-07-12 |
| CN100387488C true CN100387488C (en) | 2008-05-14 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB2004800157765A Expired - Fee Related CN100387488C (en) | 2003-06-06 | 2004-05-26 | Method for supporting a propelled flying object during take-off and/or landing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN100387488C (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1709058A (en) * | 1926-07-17 | 1929-04-16 | Brunner Frederick | Landing method for aircraft |
| GB343763A (en) * | 1929-03-02 | 1931-02-26 | Roger Beaucaire | A new or improved method of facilitating the starting and landing of aeroplanes and apparatus therefor |
| US4700912A (en) * | 1986-04-24 | 1987-10-20 | Grumman Aerospace Corporation | Laser illumination system for aircraft launch and landing system |
| EP0579508A1 (en) * | 1992-07-16 | 1994-01-19 | British Aerospace Public Limited Company | Landing of aircraft |
-
2004
- 2004-05-26 CN CNB2004800157765A patent/CN100387488C/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1709058A (en) * | 1926-07-17 | 1929-04-16 | Brunner Frederick | Landing method for aircraft |
| GB343763A (en) * | 1929-03-02 | 1931-02-26 | Roger Beaucaire | A new or improved method of facilitating the starting and landing of aeroplanes and apparatus therefor |
| US4700912A (en) * | 1986-04-24 | 1987-10-20 | Grumman Aerospace Corporation | Laser illumination system for aircraft launch and landing system |
| EP0579508A1 (en) * | 1992-07-16 | 1994-01-19 | British Aerospace Public Limited Company | Landing of aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN1802287A (en) | 2006-07-12 |
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