CN104554753A - General aircraft linear motor traction take-off acceleration launching device - Google Patents
General aircraft linear motor traction take-off acceleration launching device Download PDFInfo
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- CN104554753A CN104554753A CN201310468153.4A CN201310468153A CN104554753A CN 104554753 A CN104554753 A CN 104554753A CN 201310468153 A CN201310468153 A CN 201310468153A CN 104554753 A CN104554753 A CN 104554753A
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Abstract
The invention discloses a general aircraft linear motor traction take-off acceleration launching device, and relates to the application field of linear motors. A launching aircraft is towed by a linear motor to obtain a take-off speed; and a take-off air injection resistance baffle plate is mounted behind the aircraft for providing auxiliary thrust to the aircraft in boosting take-off and providing auxiliary brake force to the linear motor in braking. A ground energy is used for providing energy needed by the take-off phase of the aircraft for the aircraft; and the saved energy is used for prolonging the flight distance of the aircraft or replacing to effective load of the aircraft. The device uses a decentralizing method for changing the high-power linear motor with concentrated power to a group linear motor combined by multiple low-power linear motors to replace the high-power linear motor with concentrated power, so that the manufacturing difficulty of the launching device on such key parts as the linear motor, a current breaker and a direct current-alternating current frequency modulation inverter is reduced, and the system reliability is improved.
Description
Technical field
The present invention relates to linear motor technical field, is linear electric motors are applied to general purpose vehicle linear electric machine traction to take off acceleration catapult-launching gear specifically.
Background technology
Because the aircraft takeoff stage needs the very high acceleration/accel that takes off, average energy consumption when therefore energy consumption is much higher than normal vehicle operation.Therefore for a long time, people find a kind of method always, provide energy resource supply aircraft energy needed for takeoff phase by ground, save aircraft and carry energy resource consumption, to increase the flying distance of aircraft, increase the capacity weight of aircraft.Aircraft needs very large thrust in takeoff phase, requires that traction power provides great instantaneous power.Do aircraft takeoff ejection power with linear electric motors, by the restriction of linear electric motors volume requirement and insulating material, it is very high that the voltage of linear electric motors can not design.By electric power formula: power=voltage * electric current can be inferred, very big at moment impact power, when voltage is not high, its inrush current is inevitable very huge, the electric current that disjunction is so huge, proposes very high requirement to the safe in operation of current breaker or inverter and reliability.When circuit breaker or inverter need continuous frequent operation, the property safe and reliable to operation of current breaker and inverter will become the key taking off ejection system, once circuit breaker or inverter et out of order, whole ejection system of taking off may be caused to paralyse comprehensively.With regard to current electromagnetic ejection system technology, high-capacity current breaker and inverter are to become the technical bottleneck of electromagnetic ejection system.
The present invention adopts the method broken the whole up into parts, by the high-performance linear electric motors of concentrated power, by rational structure design, change into some low power linear electric motors, be combined into and make a concerted effort to meet the group's linear electric motors launching needs, substitute the high-power linear electric motors concentrating power, reduce the manufacture difficulty of linear electric motors, circuit breaker and inverter, the reliability of support system.
Table 1: when three-phase alternating current single-sided linear electrical motor input ratio is for 50N/KVA, different quality, different takeoff speed, the departure time needed for different acceleration/accel, thrust, linear electric motors power and take off distance.The bilateral linear motor input of three-phase alternating current is than being 78N/KVA, and required straight line electric acc power can decrease than lower apparent power.
| Vehicle mass t | Speed KM/h | Acceleration/accel rice * second square | The second departure time | Thrust KN | Power KVA | Take off distance M |
| 1.00 | 300.00 | 29.43 | 2.83 | 29.43 | 588.60 | 117.98 |
| 1.00 | 500.00 | 29.43 | 4.72 | 29.43 | 588.60 | 327.73 |
| 1.00 | 500.00 | 49.05 | 2.83 | 49.05 | 981.00 | 196.64 |
| 20.00 | 300.00 | 29.43 | 2.83 | 588.60 | 11,772.00 | 117.98 |
| 400.00 | 300.00 | 3.00 | 27.78 | 1,200.00 | 24,000.00 | 1,157.41 |
| 400.00 | 300.00 | 1.50 | 55.56 | 600.00 | 12,000.00 | 2,314.81 |
As can be seen from Table 1, quality is the aircraft of 1 ton, acceleration/accel is 3g (29.43 meters of second square), takeoff speed is 300KM/h, the departure time is 2.83 seconds, take off distance is 117.98 meters, need thrust 29.43KN, the input of single-sided linear electrical motor, than being 50N/KVA [1], needs three-phase alternating current linear motor apparent power 588.60KVA, voltage 1000V, apparent current 339.84A, power factor is considered by 0.5, and active volt-amperes is 294.3KW, is equivalent to No. 4,2 Guangzhou line light rail linear motor (150KW/ platform).On this power level, linear electric motors and corresponding inverter technology are all the technology of mature and reliable.As reference, quality is the aircraft of 20 tons, approximately needs 20 power to be the linear motor of 150KW.By group of the present invention linear electric motors, Figure of description 3 level installs double-deck superposition 4 bilateral linear motors 35, and only need 1 row, 2 layer of 5 row can lay group's linear electric motors 3 of 20 150KW, its engineering structure, utilizes existing engineering technology, can realize completely.If motor is installed the number of plies to be increased to 3 layers, the linear motor 3 of 30 150KW can be installed, in theory can in 2.83 seconds, in the distance of 117 meters, the aircraft of 30 tons is launched in traction.Under centralized computer control, by 30 technology maturations, voltage, at the inverter of 1100V, controls group's linear motor 3 of 30 150KW, with regard to prior art, without any problem.With Boeing-747-400 maximum take-off weight 400 tons calculating, the linear motor (3) of 20 150KW, in theory can in 55.56 seconds, with the acceleration/accel of 1.5 meters of seconds square, in the take off distance of 2314.81, by Boeing-747-400 aircraft of 400 tons, accelerate to the takeoff speed of 300 kilometers, and the Take-Off Field Length of Boeing-747-400 is 3018 meters, takeoff speed is 280-300KM/h.
Summary of the invention
For the present situation of current aircraft Electromagnetical ejector, the object of the invention is with the little group's linear electric motors of multiple stage power, substitute separate unit high-power linear electric motors aircraft electromagnetism ejection mode, thus solving the technical bottleneck of current electromagnetic ejection system, high-power current breaker and inverter manufacture the technical barrier of difficulty.With existing, the electromagnetic ejection system of proven technique Realization of Product high thrust.
Accompanying drawing explanation
The present invention has following accompanying drawing:
Fig. 1 general purpose vehicle linear electric machine traction takes off and accelerates catapult-launching gear lateral plan
Fig. 2 general purpose vehicle linear electric machine traction takes off and accelerates catapult-launching gear birds-eye view
Fig. 3 general purpose vehicle linear electric machine traction takes off and accelerates catapult-launching gear cross sectional drawing
Reference numeral:
1 is aircraft, and 2 is ground flying runway, flight deck or launcher unit, and 3 is linear electric motors, and 4 is the jet resistance baffle plate that takes off.
Detailed description of the invention
At ground runway, under flight deck or anchor fitting, linear motor is installed, by longitudinally connecting device and multiple linear electric motors are connected composition groups linear electric motors by horizontal connecting device, combine for aircraft provides enough tractive forces, aircraft is made to obtain enough takeoff speeds, take off jet resistance baffle plate under the traction of group's linear electric motors with aircraft synchronized operation, air-flow antagonistic force is utilized to provide augmented thrust for aircraft, the last moment on ground is flown away from aircraft, linear electric motors enter brake running state, airflow acting force provides additional braking force for linear electric motors.
Below in conjunction with accompanying drawing, the present invention is described in further detail.
Fig. 1 is that general purpose vehicle linear electric machine traction takes off and accelerates catapult-launching gear lateral plan, aircraft 1 to be placed on ground runway, flight deck or launcher 2 when taking off, the tractive force that linear electric motors 3 produce makes aircraft 1 obtain takeoff speed, the jet resistance baffle plate 4 that takes off is corresponding with aircraft engine, utilizes air-flow reaction thrust to provide augmented thrust for aircraft.Fig. 2 is that general purpose vehicle linear electric machine traction takes off and accelerates catapult-launching gear birds-eye view, by longitudinal adaptor union 22 and horizontal unitor 23, multiple stage linear electric motors are formed group's linear electric motors 21, tandem motor connects, for preposition linear electric motors provide additional braking force when braking by connecting device 24.Fig. 3 is that general purpose vehicle linear electric machine traction takes off and accelerates catapult-launching gear cross sectional drawing, 31 is level installation individual layer two bilateral linear motors, 32 is at right angle setting individual layer separate unit bilateral linear motor, 33 is level installation individual layer two single-sided linear motors, 34 is at right angle setting bilayer superposition two bilateral linear motors, and 35 install bilayer for level superposes 4 bilateral linear motors.。
On the basis of technique scheme, said aircraft can be can in atmosphere and the various aircraft of too airflight.
On the basis of technique scheme, the size that the number of motors of said group linear electric motors requires according to takeoff thrust and determining.
On the basis of technique scheme, the said jet resistance baffle plate that takes off only is arranged in case of need.
Technical characterstic of the present invention is as follows:
1.1 group's linear electric motors methods, the corresponding inverter of every platform linear electric motors, under centralized computer control, easily realizes Time-sharing control and runs, make the thrust output of linear electric motors be able to accurate control, thus better control the acceleration/accel that takes off of aircraft.
1.2 take off jet resistance baffle plate take off accelerate time can provide augmented thrust, can additional braking force be provided when linear electric motors are braked.
General purpose vehicle straight line electric machine travel of the present invention promotes to take off and accelerates catapult-launching gear major advantage and be:
2.1 reduce electromagnetic ejection system to the power requirement of linear electric motors, and then reduce the power requirement to inverter, and high-power inverter is considered to the technical bottleneck of aircraft electromagnetic ejection system.
2.2, with the energy that takes off of ground energy substitution aircraft, can extend the flying distance of aircraft or increase the capacity weight of aircraft.For Boeing-747-400, maximum fuel capacity is 216840 liters, and period energy consumption of taking off is considered by 5%, takes off with linear electric machine traction, can fuel saving 10842 liters, by every gas mileage 16.1 liters calculating, can extend flying distance 5% about 673 kilometers.Aviation kerosene proportion is by 1.282 liters of/kilogram of calculating, and 10842 liters are roughly equal to 8457 kilograms, by each passenger 100 kilograms calculating, can increase by 104 passengers, calculates by Boeing-747-400 passenger capacity 416 people, increases passenger capacity about 25%.
Claims (3)
1. a general purpose vehicle linear electric machine traction takes off acceleration catapult-launching gear, it is characterized in that: linear electric motors (3) are arranged on below ground, flight deck or anchor fitting (2), aircraft (1) above linear electric motors (3) traction, promotion ground, flight deck or anchor fitting, makes aircraft (1) obtain takeoff speed.
Described aircraft (1) refers to fly in earth atmosphere, or can the manual implement of extra-atmospheric flight.
2. linear electric motors as claimed in claim 1, can separate unit linear electric motors, may also be the group's linear electric motors be combined into by connecting device by multiple stage linear electric motors.
3. in aircraft (1) rear end, can install setting and to take off jet resistance baffle plate (4), jet resistance baffle plate (4) of taking off is drawn by linear electric motors (3) and is promoted.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310468153.4A CN104554753A (en) | 2013-10-10 | 2013-10-10 | General aircraft linear motor traction take-off acceleration launching device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310468153.4A CN104554753A (en) | 2013-10-10 | 2013-10-10 | General aircraft linear motor traction take-off acceleration launching device |
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| CN104554753A true CN104554753A (en) | 2015-04-29 |
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| CN201310468153.4A Pending CN104554753A (en) | 2013-10-10 | 2013-10-10 | General aircraft linear motor traction take-off acceleration launching device |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2479138B1 (en) * | 1980-04-01 | 1983-06-10 | Andre Gilbert | |
| US4678143A (en) * | 1982-12-17 | 1987-07-07 | Frazer-Nash Ltd. | Launcher for remotely piloted aircraft |
| CA2328669A1 (en) * | 2000-12-15 | 2002-06-15 | Florencio Neto Palma | Airport takeoff-landing assisting shuttle |
| CN103057722A (en) * | 2013-01-08 | 2013-04-24 | 上海大学 | Active maglev electromagnetic catapult |
| CN103359297A (en) * | 2012-03-30 | 2013-10-23 | 卢振江 | Combined catapult for aircraft carriers |
-
2013
- 2013-10-10 CN CN201310468153.4A patent/CN104554753A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2479138B1 (en) * | 1980-04-01 | 1983-06-10 | Andre Gilbert | |
| US4678143A (en) * | 1982-12-17 | 1987-07-07 | Frazer-Nash Ltd. | Launcher for remotely piloted aircraft |
| CA2328669A1 (en) * | 2000-12-15 | 2002-06-15 | Florencio Neto Palma | Airport takeoff-landing assisting shuttle |
| CN103359297A (en) * | 2012-03-30 | 2013-10-23 | 卢振江 | Combined catapult for aircraft carriers |
| CN103057722A (en) * | 2013-01-08 | 2013-04-24 | 上海大学 | Active maglev electromagnetic catapult |
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Application publication date: 20150429 |
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