WO2007043463A1 - 加速装置 - Google Patents
加速装置 Download PDFInfo
- Publication number
- WO2007043463A1 WO2007043463A1 PCT/JP2006/320080 JP2006320080W WO2007043463A1 WO 2007043463 A1 WO2007043463 A1 WO 2007043463A1 JP 2006320080 W JP2006320080 W JP 2006320080W WO 2007043463 A1 WO2007043463 A1 WO 2007043463A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- aircraft
- support base
- acceleration device
- acceleration
- power
- Prior art date
Links
- 230000001133 acceleration Effects 0.000 title claims abstract description 110
- 230000000452 restraining effect Effects 0.000 claims description 18
- 238000005339 levitation Methods 0.000 claims description 7
- 230000005484 gravity Effects 0.000 claims description 6
- 230000000630 rising effect Effects 0.000 claims 1
- 210000001364 upper extremity Anatomy 0.000 description 12
- 238000006243 chemical reaction Methods 0.000 description 7
- 238000010586 diagram Methods 0.000 description 3
- 230000003993 interaction Effects 0.000 description 3
- 238000000926 separation method Methods 0.000 description 3
- 239000000446 fuel Substances 0.000 description 2
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 1
- 206010034719 Personality change Diseases 0.000 description 1
- 230000005856 abnormality Effects 0.000 description 1
- 239000006096 absorbing agent Substances 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 239000003990 capacitor Substances 0.000 description 1
- 239000004020 conductor Substances 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 229910052744 lithium Inorganic materials 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 230000001141 propulsive effect Effects 0.000 description 1
- 230000001172 regenerating effect Effects 0.000 description 1
- 238000009991 scouring Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft
- B64F1/10—Ground or aircraft-carrier-deck installations for launching aircraft using self-propelled vehicles
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/80—Energy efficient operational measures, e.g. ground operations or mission management
Definitions
- the present invention relates to an acceleration device, and more particularly to an acceleration device that can safely and efficiently accelerate even an aircraft that lacks lift in a low speed region such as a supersonic passenger aircraft.
- Patent Document 1 Take-off assist device (Patent Document 1) in which the primary coil of the linear motor is installed on one of the airframe and the runway, and the secondary coil of the linear motor is installed on the other
- a jet engine that heats the propellant with laser light to obtain thrust and a laser term introducing portion that receives the irradiated laser light are provided in a carriage for mounting a flying object, and laser light irradiation is performed in the middle of the trajectory on which the carriage travels.
- a flying object acceleration device provided with a mechanism Patent Document 2 has been proposed.
- Patent Document 1 JP-A-5-16897
- Patent Document 2 Japanese Patent No. 2861569
- the supersonic passenger aircraft is large in size and weight, and therefore takes off at a high speed. Therefore, it accelerates to a predetermined speed on a narrow runway and takes off. If this happens, it is necessary to safely stop the supersonic passenger aircraft. To do so, the aircraft must be restrained until the supersonic passenger aircraft is accelerated to takeoff speed. In addition, even if acceleration is stopped halfway and the aircraft is stopped, it is necessary to be surely restrained until the aircraft stops.
- the present invention has been made to solve the above-described problems, and an object of the present invention is to provide an acceleration device that can accelerate safely and efficiently even with a high-speed and heavy aircraft.
- the invention according to claim 1 is an accelerating device for accelerating and starting an aircraft, and supports the aircraft so that the aircraft is not retracted or levitated during acceleration and the force is not pitched.
- a guide way provided along the path, guide means for guiding the support base along the guide way, and drive means for driving the support base along the guide way.
- the present invention relates to a characteristic acceleration device.
- the support base travels along the guide way while the aircraft is held on the support base so that the aircraft does not move backward from the support base, float, or pitch. Let it accelerate.
- the aircraft can be stopped by decelerating the support base in the driving means, so that the safety is high.
- the invention according to claim 2 relates to the acceleration device according to claim 1, wherein the guide means is a levitating guide coil and the driving means is a force S linear motor.
- the linear motor used as the driving means in the acceleration device has a maximum acceleration due to the adhesion coefficient between the rail and the wheel, unlike a normal rail-wheel driving system. Since there is no limitation, the acceleration of the support base can be set based on the length of the guide wheel and the speed at which the aircraft leaves. In addition, since the upper / lower / left / right guide means are magnetic panels using floating guide coils, the support can be guided in a non-contact manner except in a low speed range.
- the invention according to claim 3 is configured so that the aircraft is restrained so as not to be lifted from the support base and the force is not retracted, and the aircraft can freely move in the disengagement direction at the time of disengagement.
- the aircraft In the acceleration device, the aircraft is supported by the aircraft restraining means without being retracted, levitated, or pitched on a support base. However, since the aircraft can move freely in the direction of departure when leaving the aircraft, if the support base is decelerated after reaching the take-off speed of the aircraft, the aircraft will move forward due to inertial force.
- the aircraft is held on the support base without being retracted, lifted up, or pitched, and is used for removing the aircraft from the support base after completion of acceleration. No special mechanism is required.
- the invention according to claim 4 relates to the acceleration device according to claim 3, wherein the aircraft restraining means restrains the aircraft so as not to move in the departure direction during acceleration.
- the aircraft In the acceleration device, during acceleration, the aircraft is restrained so that it does not move in the departure direction by the aircraft restraining means, so that the takeoff speed of the aircraft is not reached for some reason. Even if the acceleration decreases or the acceleration stops, the aircraft will not leave the support base. Further, when the support base reaches the take-off speed of the aircraft, the restraint in the separation direction is released, so that the aircraft restraining means does not interfere with the separation of the aircraft from the support base.
- the invention according to claim 5 is characterized in that the aircraft restraining means is in front of the center of gravity of the aircraft, forward restraining means for restraining the aircraft, and near the center of gravity of the aircraft. 5.
- the attitude change of the aircraft during acceleration can be effectively prevented.
- aircraft Even if there is a difference in the aircraft restraint means, the burden is small! / ⁇ .
- the invention according to claim 6 is a claim in which a plurality of the guideways are provided in parallel to each other, and the guide means supports the support base over the plurality of guideways. 5.
- the aircraft to be accelerated is a four-engine aircraft and one of the four engines fails, the engine thrust of the aircraft supported by the support base and the propulsive force of the drive means are not included.
- the support base is supported across the plurality of guideways by the guide means, and is generated along the guideway. Therefore, the aircraft can be safely stopped when the unbalanced load in the above direction occurs.
- the invention according to claim 7 relates to the acceleration device according to any one of claims 1 to 6, wherein the driving means brakes the support base by electric braking.
- the driving means brakes the support base by electric braking, so that deceleration and braking can be performed without contact.
- each driving means includes two or more power converters for supplying electric power.
- each driving means is supplied with a plurality of power conversion device powers. Therefore, even if one power conversion device fails in a certain driving means, the acceleration of the aircraft can be continued. Further, if the driving means is divided into a plurality of sections and the power of the power converter is supplied to each section, the section length of the driving means can be shortened, and an increase in applied voltage can be suppressed.
- the invention according to claim 9 relates to the acceleration device according to claim 8, further comprising a power absorbing device that absorbs electric power generated by applying electric braking in the driving means.
- the invention according to claim 10 relates to the acceleration device according to claim 8 or 9, further comprising a power storage device that stores in advance power for driving the driving means.
- the acceleration device in addition to the power received by the power receiving facility, power can be discharged from the power storage device and supplied to the driving means. Therefore, if the capacity of the power receiving facility is the same, a large amount of power is generated by the driving means. Can supply. Therefore, it is suitable for accelerating and starting high-speed and heavy aircraft such as supersonic passenger aircraft. Further, if the amount of power supplied to the driving means is the same, the capacity of the power receiving facility can be reduced.
- the invention according to claim 11 relates to the acceleration device according to claim 9, wherein the power absorbing device is a flywheel.
- the invention according to claim 12 relates to the acceleration device according to claim 9, wherein the flywheel is also used as a power storage device.
- the electric power generated during the electric braking in the driving means is recovered as a mechanical rotation of the flywheel. Therefore, by increasing the weight and diameter of the flywheel, large electric power is also effective. Can be recovered. The lifetime is also semi-permanent. And since the electric power collect
- the flywheel can store a large amount of power as described above, it is suitable as a power storage device.
- the invention according to claim 13 relates to the acceleration device according to any one of claims 1 to 12, wherein the aircraft is separated from the support base at a predetermined angle of attack.
- the acceleration device since the aircraft is launched obliquely upward, the travel distance of the support base can be shortened. Therefore, the length of the guideway can be shortened.
- the invention according to claim 14 relates to the acceleration device according to any one of claims 1 to 12, wherein the aircraft is horizontally detached from the support base.
- the acceleration device Since the aircraft is accelerated in a horizontal state, the acceleration device has less acceleration resistance than the case where the aircraft is accelerated by holding the aircraft at a predetermined angle of attack. Less burden on the support base. [0040] In the invention according to claim 15, the support base accelerates and starts the aircraft in one direction along the guideway or in another direction opposite to the one direction. ⁇
- the acceleration direction of the aircraft can be selected from the one direction and the other direction according to the wind direction.
- the invention according to claim 16 is provided with any one of claims 1 to 15, comprising support means for supporting the support base in a downward force when an aircraft is placed on the support base. This relates to the acceleration device.
- the support base is supported downward by the support means. It is possible to prevent an excessive load from being applied to the means and the driving means.
- the support means include a jack.
- an acceleration device that can safely and efficiently accelerate even a high-speed and heavy aircraft.
- FIG. 1A is a plan view showing a supersonic passenger aircraft placed on the acceleration device according to the first embodiment.
- FIG. 1B is a side view showing a supersonic passenger aircraft placed on the acceleration device according to the first embodiment.
- FIG. 2 is a perspective view showing a configuration of a carriage provided on a support base in the acceleration device shown in FIG. 1.
- FIG. 3 is a cross-sectional view showing a relative positional relationship between the carriage and the guide wheel in the acceleration device shown in FIG. 1.
- FIG. 4 is a perspective view showing a configuration of a guide way included in the acceleration device shown in FIG. 1.
- FIG. 5 is a perspective view showing the positional relationship and form between the levitation guide coil and the propulsion coil in the guide way provided in the acceleration device shown in FIG. 1.
- FIG. 6 is an explanatory diagram showing a feeder system in the acceleration device shown in Fig. 1.
- FIG. 7 is a schematic diagram showing a configuration of a power converter and its surroundings in the feeder system shown in FIG.
- FIG. 8 is an explanatory view showing a state where a supersonic passenger aircraft is mounted on a support base in the acceleration device shown in FIG.
- FIG. 9 is an explanatory view showing a state where a supersonic passenger aircraft is fixed to the support base and acceleration is started.
- FIG. 10 is an explanatory diagram showing a state where the engine of the supersonic passenger aircraft is fully opened in the state shown in FIG.
- FIG. 11 is an explanatory view showing a state where the front leg of the main landing gear provided on the support base is retracted and the restraint on the front side of the supersonic passenger aircraft is released.
- FIG. 12 is an explanatory view showing a supersonic passenger plane being detached from the support base.
- FIG. 13 is an explanatory view showing that the support base is decelerating after the supersonic passenger aircraft is detached.
- FIG. 14 is a run curve of the support base.
- FIG. 15 is a side view showing another example of the acceleration device according to the first embodiment.
- FIG. 16 is an explanatory view showing a state where one of the upper coils mounted on the carriage during travel on the guideway is turned in the acceleration device according to the first embodiment.
- the acceleration device 100 corresponds to the support base 2 on which the supersonic passenger aircraft 1000 is placed and the guide way in the present invention, and guides the support base 2. 4 guideway 4 is provided.
- the aircraft that can be accelerated by the accelerator 100 is not limited to the supersonic passenger aircraft 1000, and can be used for ordinary subsonic passenger aircraft.
- the passenger plane mounting portion 2A that supports the supersonic passenger aircraft 1000 during acceleration occupies the first half along the acceleration direction a of the supersonic passenger aircraft 1000.
- the passenger plane mounting portion 2A is inclined upward along the acceleration direction a, and is provided with a front leg stocker 6 and a main leg stocker 8.
- the front leg stopper 6 and the main leg stopper 8 are compatible with the aircraft restraint means in the present invention.
- the front leg stopper 6 corresponds to the forward restraining means
- the main leg stopper 8 corresponds to the central restraining means.
- the front leg stopper 6 and the main leg stopper 8 respectively hold the rear wheel 1002 and the main wheel 1004 of the supersonic passenger aircraft 1000 along the acceleration direction a, and the upper end is forward toward the front wheel 1002 and the main wheel 1004.
- the front wheel 1002 and the main wheel 1004 can be constrained from above.
- Both the front leg strut 6 and the main leg strut 8 are formed on the support 2 so as to be concealed!
- a main leg front stopper 10 that restrains the main wheel 1004 also in front force is provided.
- the front landing gear stopper 10 is also provided so that it can be concealed.At the time of acceleration, it protrudes from the passenger aircraft mounting part 2A as shown in Fig. 1, but the acceleration ends and the supersonic passenger aircraft 1000 disengages from the support base 2. When doing so, it will be pulled into passenger plane mounting part 2A so as not to interfere with the separation of supersonic passenger plane 1000.
- the carriage 12 is provided with a carriage frame 13 formed in a ladder shape, a vehicle upper coil 14 provided on a side surface of the carriage frame 13, and an upper surface of the carriage frame 13. And an air panel 15 for supporting the base 2.
- the vehicle upper side coil 14 is a superconducting coil, and is provided on a side surface of the bogie frame 13, five in total, ten in total.
- a total of 10 air panels 15 are provided in two rows of five.
- tire wheels 16 for low-speed running are provided on the lower surface of the carriage frame 13.
- a stopper 17 and a stopper 18 for preventing the carriage 12 from coming into contact with the guideway 4 when the vehicle upper side coil 14 is turned are provided in the vicinity of both side edges of the upper surface of the carriage frame 13 and in the center of the lower surface. Is provided.
- the guideway 4 includes a slab portion 44 provided with a pair of parallel traveling paths 42 on which the tire wheels 16 provided on the carriage 12 travel at a low speed. And a guide wall 40 erected on the slab portion 44 so as to sandwich the travel path 42 therebetween.
- a propulsion coil 41 and a floating guide coil 43 are provided with force.
- the levitation guide coil 43 overlaps the wall of the propulsion coil 41 Is provided.
- the tire wheel 16 can run sufficiently even if the carriage 12 does not lift up the guideway 4 force.
- the levitation guide coil 43 is omitted.
- the propulsion coil 41 and the levitation guide coil 43 correspond to the driving means and guide means in the present invention, respectively.
- the propulsion coil 41 is a coil in which a conductor wire is wound in a frame shape, and the levitation guide coil 43 has four pieces wound in the same direction, for example, in a counterclockwise direction. It has a configuration in which four frame-shaped coils are combined in a U-shape, and the carriage 12 is buoyant by electromagnetic interaction with the upper coil 14 provided on the carriage frame 13, and the support base 2 is then levitated.
- each guide window 4 is supplied with AC power from the four power converters 50A, 50B, 50C and 50D to the propulsion coil 41 as shown in FIG. 2 is driven.
- the propulsion coil 41 is alternately divided into section A and section C, and the propulsion coil 41 in section A is connected to the power converter 50A. Therefore, the propulsion coil 41 in section C is supplied with power from the power converter 50C.
- the propulsion coil 41 is alternately divided into a section B and a section D.
- the propulsion coil 41 of the section B is separated from the power converter 50B, and the propulsion coil 41 of the section D is Power converter 50D power is also fed.
- a generator motor 51 that rotates a flywheel 52 is provided in the power converters 50A, 50B, 50C, and 50D (hereinafter sometimes collectively referred to as "power converter 50"). It is connected.
- the flywheel 52 and the generator motor 51 correspond to the power absorbing device in the present invention.
- SMES is also used as a power absorber.
- the propulsion coil 41 operates as a power generation coil, and the resulting alternating current is converted into alternating current of a predetermined frequency by the power conversion device 50, the generator motor 51 is driven, and the flywheel 52 rotates.
- the carriage 12 is driven at the propulsion coil 41, the inertial force of the flywheel 52 is added to the three-phase AC from the power receiving facility 60. Accordingly, the alternating current generated by the rotation of the generator motor 51 is supplied to the power converter 50.
- a capacitor, a superconducting coil, a lithium battery, or the like can be used as a power absorbing device instead of the combination of the generator motor 51 and the flywheel 52.
- the supersonic passenger aircraft 1000 is pulled up to the passenger aircraft placement portion 2 A of the support base 2. At this time, it is preferable that the front leg stocker 6, the main leg stocker 8, and the front leg stocker 10 are retracted.
- the supersonic airliner 1000 can be pulled up by an appropriate means such as a winch or pulled by a towing vehicle that can be driven by engine thrust.
- a large number of jacks 70 are provided between the guide wall 40 and the support base 2 so that the support base 2 is not squeezed or excessive load force is applied to the carriage 12, for example, the example of FIG. Then, insert 9 on one side and 18 on both sides, and support 2 from below.
- the jack 70 corresponds to the support means in the present invention.
- supersonic passenger aircraft 1000 When supersonic passenger aircraft 1000 is restrained by support base 2, power is supplied to propulsion coil 41 by power converter 50 in four-way guideway 4, and acceleration is started as shown in Figs.
- the acceleration at this time can be set to 0.6G, for example, but if you want to take off at a short distance, set the acceleration higher than 0.6G. On the other hand, if you do not want passengers to feel discomfort due to sudden acceleration, The acceleration can be set smaller than 0.6G.
- the engine of the supersonic passenger aircraft 1000 may be started before the start of acceleration, but may be stopped at the start of acceleration as shown in FIG. 9 and the engine may be started after the start of acceleration.
- Figure 10 The supersonic airliner 1000 engine is shown fully open.
- the supersonic passenger aircraft 1000 When the engine is fully opened, the supersonic passenger aircraft 1000 receives a force to move forward on the support base 2 due to the engine thrust, but the main wheel 1004 is restrained by the main leg front stopper 10 in the forward direction. Acceleration at 0.6G will continue in the same state as 2. Then, when it is confirmed that the engine is fully opened, as shown in FIG. 10, when the engine stalls, the acceleration is stopped and the support base 2 is stopped.
- the acceleration of the support base 2 is reduced, and at the same time, the main landing gear stopper 10 is retracted as shown in Figs.
- the front landing gear stop 10 By retracting the front landing gear stop 10, the supersonic passenger aircraft 1000 is released from the restraint on the front side, and therefore the support 2 is moved forward by the thrust of the engine in the fully open operation, as shown in FIGS. As shown in Fig. 12, take off from the support base 2 and take off and ascend.
- the support base 2 is decelerated at a high deceleration of about 0.8G, for example.
- the acceleration device 100 for example, two support bases 2 are provided so as to be back to each other, and are run along directions opposite to each other, whereby a supersonic passenger aircraft is provided. It is also possible to form 1000 so that it can be accelerated in both directions.
- the acceleration device 100 according to the aspect has a feature that the acceleration direction of the supersonic passenger aircraft 1000 can be selected from the two directions according to the wind direction. For example, when accelerating the supersonic passenger aircraft 1000 in the direction of arrow a in FIG.
- the left half of the support platform 2 is the passenger aircraft mounting section 2A, and the arrows When accelerating in the direction opposite to a, the right half of the support base 2 may be inclined so as to rise along the acceleration direction with respect to the horizontal plane as the passenger aircraft mounting portion 2A.
- front wheel 1002 and main wheel 1004 of supersonic passenger aircraft 1000 are restrained by the rear and upper sides by front leg stopper 6 and main leg stopper 8.
- the main wheel 1004 is also restrained from the front side force by the front leg stop 10.
- the supersonic passenger aircraft 1000 is not retreated on the support base 2, is not lifted, and is accelerated without pitching.
- the airframe and the support base 2 are held together so that the airframe is not detached from the support base 2 by the engine thrust. Acceleration can be continued.
- the support base 2 can be accelerated while holding the carriage 12 and the guideway 4 in a non-contact manner.
- the power conversion device 50 is operated so that the phase angle force of the current from the propulsion coil 41 advances beyond the phase angle of the power supplied from the power conversion device 50, strong regenerative braking is applied.
- the supersonic airliner 1000 has some trouble and it is impossible to take off, it is very easy to stop the support base 2 without removing the supersonic airliner 1000 from the support base 2. Therefore, safety is extremely high.
- each guideway 4 is supplied with power by four power converters 50, one of the power converters 50 can be obtained by dividing the guideway 4 into short sections. Acceleration can be continued even if a failure occurs.
- the surplus power in the propulsion coil 41 is recovered by the rotation of the flywheel 52 via the generator motor 51 and used for the next acceleration.
- the peak load can be reduced, and the power receiving facility 60 does not need to be significantly expanded.
- the acceleration device of the present invention can be used for take-off assistance of a normal subsonic passenger aircraft as well as a supersonic passenger aircraft.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Arrangement Or Mounting Of Propulsion Units For Vehicles (AREA)
- Platform Screen Doors And Railroad Systems (AREA)
- Linear Motors (AREA)
- Control Of Vehicles With Linear Motors And Vehicles That Are Magnetically Levitated (AREA)
- General Electrical Machinery Utilizing Piezoelectricity, Electrostriction Or Magnetostriction (AREA)
- Vibration Prevention Devices (AREA)
Abstract
Description
Claims
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/089,996 US8028953B2 (en) | 2005-10-12 | 2006-10-06 | Accelerating device |
CN2006800378574A CN101300173B (zh) | 2005-10-12 | 2006-10-06 | 加速装置 |
BRPI0617328-4A BRPI0617328A2 (pt) | 2005-10-12 | 2006-10-06 | dispositivo de aceleração |
CA2625369A CA2625369C (en) | 2005-10-12 | 2006-10-06 | Accelerating device |
EP06811407.3A EP1935785A4 (en) | 2005-10-12 | 2006-10-06 | ACCELERATION DEVICE |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2005298030A JP4624232B2 (ja) | 2005-10-12 | 2005-10-12 | 加速装置 |
JP2005-298030 | 2005-10-12 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2007043463A1 true WO2007043463A1 (ja) | 2007-04-19 |
Family
ID=37942706
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/JP2006/320080 WO2007043463A1 (ja) | 2005-10-12 | 2006-10-06 | 加速装置 |
Country Status (8)
Country | Link |
---|---|
US (1) | US8028953B2 (ja) |
EP (1) | EP1935785A4 (ja) |
JP (1) | JP4624232B2 (ja) |
CN (1) | CN101300173B (ja) |
BR (1) | BRPI0617328A2 (ja) |
CA (1) | CA2625369C (ja) |
RU (1) | RU2413659C2 (ja) |
WO (1) | WO2007043463A1 (ja) |
Cited By (2)
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CN112179634A (zh) * | 2020-09-22 | 2021-01-05 | 中国特种飞行器研究所 | 一种基于无人发射车的水上迫降试验装置及方法 |
CN114348293A (zh) * | 2021-12-30 | 2022-04-15 | 中国特种飞行器研究所 | 一种基于无人弹射装置的水上迫降试验系统及试验方法 |
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US7344744B2 (en) | 2003-04-16 | 2008-03-18 | Kraft Foods Holdings, Inc. | Resealable food container with tamper-evident indicator |
US8141850B2 (en) * | 2008-10-24 | 2012-03-27 | Mojack Distributors, Llc | Apparatuses and methods for an improved vehicle jack |
CN102862684A (zh) * | 2011-07-05 | 2013-01-09 | 王长存 | 新型航空母舰起飞甲板 |
FR2990929B1 (fr) * | 2012-05-24 | 2015-01-09 | Michel Steinbrucker | Systeme d'assistance a l'atterrissage et/ou au decollage d'avions, comprenant une plate-forme automotrice mue par des moteurs electriques alimentes par des rails de guidage |
US9079671B2 (en) * | 2013-01-22 | 2015-07-14 | Exhaustless, Inc. | Aircraft thrust, assembly, and methods |
US9156564B2 (en) * | 2013-01-22 | 2015-10-13 | Exhaustless, Inc. | Airport capacity from takeoff assist |
FR3006990B1 (fr) * | 2013-06-14 | 2015-07-17 | Eads Europ Aeronautic Defence | Dispositif pour le deplacement au sol des aeronefs |
CN104176266A (zh) * | 2014-08-06 | 2014-12-03 | 廖兴华 | 航母舰载机卷扬拖动加速起飞装置 |
US10059465B2 (en) * | 2014-11-19 | 2018-08-28 | The Boeing Company | System to accelerate and decelerate aircraft for take-off and landing |
GB2555068B (en) * | 2015-08-19 | 2018-10-10 | William Hollaway John | Re-usable launch system and vehicle |
CN106542110B (zh) * | 2016-11-07 | 2018-10-12 | 北京特种机械研究所 | 飞行器人工装填装置 |
CN106697319B (zh) * | 2017-01-17 | 2023-04-11 | 张其予 | 一种飞机起飞用牵引装置 |
LU100634B1 (fr) | 2017-12-29 | 2019-07-30 | Mohamed Oujamaa | Système d'assistance aux déplacements au sol pour aéronefs |
RU2712407C1 (ru) * | 2019-04-10 | 2020-01-28 | Федеральное государственное унитарное предприятие "Крыловский государственный научный центр" | Разгонное устройство для взлета корабельных самолетов |
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- 2006-10-06 RU RU2008117689/11A patent/RU2413659C2/ru not_active IP Right Cessation
- 2006-10-06 US US12/089,996 patent/US8028953B2/en not_active Expired - Fee Related
- 2006-10-06 EP EP06811407.3A patent/EP1935785A4/en not_active Withdrawn
- 2006-10-06 CN CN2006800378574A patent/CN101300173B/zh not_active Expired - Fee Related
- 2006-10-06 CA CA2625369A patent/CA2625369C/en not_active Expired - Fee Related
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Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
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CN112179634A (zh) * | 2020-09-22 | 2021-01-05 | 中国特种飞行器研究所 | 一种基于无人发射车的水上迫降试验装置及方法 |
CN114348293A (zh) * | 2021-12-30 | 2022-04-15 | 中国特种飞行器研究所 | 一种基于无人弹射装置的水上迫降试验系统及试验方法 |
CN114348293B (zh) * | 2021-12-30 | 2023-09-05 | 中国特种飞行器研究所 | 一种基于无人弹射装置的水上迫降试验系统及试验方法 |
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US20090134274A1 (en) | 2009-05-28 |
CA2625369C (en) | 2013-11-19 |
EP1935785A4 (en) | 2013-05-08 |
JP4624232B2 (ja) | 2011-02-02 |
CN101300173B (zh) | 2010-12-01 |
RU2008117689A (ru) | 2010-01-20 |
JP2007106217A (ja) | 2007-04-26 |
CN101300173A (zh) | 2008-11-05 |
EP1935785A1 (en) | 2008-06-25 |
CA2625369A1 (en) | 2007-04-19 |
US8028953B2 (en) | 2011-10-04 |
BRPI0617328A2 (pt) | 2011-07-19 |
RU2413659C2 (ru) | 2011-03-10 |
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