CN2574996Y - Airport air navigation aiding lamp whole journey fault locating device - Google Patents
Airport air navigation aiding lamp whole journey fault locating device Download PDFInfo
- Publication number
- CN2574996Y CN2574996Y CN 02271734 CN02271734U CN2574996Y CN 2574996 Y CN2574996 Y CN 2574996Y CN 02271734 CN02271734 CN 02271734 CN 02271734 U CN02271734 U CN 02271734U CN 2574996 Y CN2574996 Y CN 2574996Y
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- Prior art keywords
- wing flap
- flow deflector
- conditioning unit
- hydraulic
- valve
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Abstract
The utility model relates to an operating device for a power boosting type ground effect aerocraft in a ground effect transition region, which comprises a hydraulic system and control circuit assembly, wherein, the hydraulic system can drive a wing flap and a prerotation vane simultaneously, and the control circuit assembly can operate, monitor and coordinate hydraulic system work. The hydraulic system comprises a hydraulic source, a coordinate control device and an actuating mechanism. Because a set of combination control systems are arranged and adopted between the wing flap and the prerotation vane, the utility model can coordinate and operate the wing flap and the prerotation vane simultaneously by only one operating switch. Namely, when the wing flap is retracted, the prerotation vane is deflected upwards by a certain rule. When the wing flap is released, the prerotation vane is deflected downwards by a certain rule. The adoption of the operating system overcomes the defect that a longitudinal moment is large caused by that the wing flap and the prerotation vane are respectively operated, which brings operating difficulty when an aerocraft flies in the transition region. The utility model not only causes the change of the longitudinal moment to be reduced greatly, but also causes operating actions by a driver to become simplified and convenient, and the utility model ensures the safety of the aerocraft when the aerocraft flies in the transition region.
Description
Technical field
The utility model relates to a kind of ground effect vehicle, and particularly a kind of power-boosting ground effect aircraft is at the operating control of ground-effect transition region flight.
Background technology
Flight " transition region " is imitated on the ground of ground effect vehicle, refers to from the configuration states of taking off of ground effect vehicle progressively to imitate the cruising flight configuration states with carrying out the transition to or progressively carry out the transition to the transition flight district of the configuration states of landing from ground effect region cruising flight configuration states.
Existing ground effect vehicle, in order to improve the starting heats performance, reduce takeoff speed, adopt the certain angle of flap deflection and the air-flow behind the screw propeller is imported the wing below, produce dynamic air cushion lift,, reduce the resistance of taxing and the get away speed of taking off to reduce the draft of hull in the starting heats process, improve the accelerating ability of take-off run, improve the takeoff data of ground effect vehicle; Ground effect vehicle take off dried up after, for the pulling force that reduces flight resistance and give full play to driving engine to improve flying speed, must pack up wing flap and with the air flow deflector behind the screw propeller to average flight state; Power-boosting ground effect aircraft landing state must deflect into the landing state from average flight state with the air-flow behind wing flap and the screw propeller again, water speed to reduce ground effect vehicle, reduces the landing impact load of ground effect vehicle.
No matter be transformed into cruising condition from takeoff condition, still be transformed into the landing state from cruising condition, all need to realize by the air flow deflector behind manipulation wing flap and the screw propeller, at this moment, variation because of air-flow, can cause the variation of the full machine moment of ground effect vehicle parallel nature, be keep the stability of ground effect vehicle, usually chaufeur at any time the operate lifting rudder with the moment balance of controlling aircraft.In the practical operation device, the air flow deflector behind wing flap folding and unfolding and the screw propeller is controlled respectively, promptly first operation of landing flaps, the air-flow behind the post deflection screw propeller.Air-flow behind operation of landing flaps and the deflection screw propeller, because of the operation time difference, can cause the change that longitudinal moment is very big, at this moment, chaufeur can only keep the flight attitude of aircraft stability and safety by the operate lifting rudder kick, but when taking off or land, because the flying speed of aircraft is less, the efficiency ratio of elevating rudder is lower, control the air-flow behind operation of landing flaps and the deflection screw propeller respectively, for guaranteeing that the required elevating rudder drift angle of longitudinal moment balance will be very big, even the maximum elevating rudder of design-calculated drift angle all is not enough to guarantee the longitudinal moment balance, and pilot control acts frequently, acutely, complicated.Chinese patent 99122366.7 has disclosed a kind of ground effect vehicle of also able to fly, this patent is focused on the aircraft that research and design has the function of soaring on the basis of original ground effect vehicle, its design improvement main points are to solve the Flight Vehicle Structure preparation when soaring, and come the existing maneuvering system of ground effect vehicle in ground-effect transition region do not proposed further solution.
Summary of the invention
The purpose of this utility model is the manipulation problem at above-mentioned existence, provide a kind of when ground-effect transition region takes off or land tunable handle the operating control of the power-boosting ground effect aircraft for ground effect transition region of air-flow behind operation of landing flaps and the deflection screw propeller simultaneously.
A kind of operating control of power-boosting ground effect aircraft for ground effect transition region, comprising can be to wing flap and flow deflector hydraulic efficiency pressure system that drives simultaneously and the control circuit assembly that can handle monitoring and coordination hydraulic work system, described hydraulic efficiency pressure system comprises hydraulic power source, cooperative control device and actuating unit, wherein:
Hydraulic power source---be used for providing pressure oil to association's actuating unit;
Cooperative control device---drive in the time of tunable control wing flap and flow deflector;
Actuating unit---can realize the execution of wing flap and flow deflector deflection action.
For making the realization that drives wing flap and flow deflector action in the hydraulic efficiency pressure system simultaneously, above-mentioned cooperative control device comprises wing flap, flow deflector conditioning unit, and described wing flap, flow deflector conditioning unit are made up of reducing valve and solenoid directional control valve, wherein:
Reducing valve---the hydraulic power source oil pressure value is reduced to actuating unit move needed operation pressure value;
Solenoid directional control valve---change the flow direction of bent liquid by the diverse location of solenoid operated spool valve.
For ease of handling, monitor and coordinate the work of hydraulic efficiency pressure system, above-mentioned control circuit assembly comprises control desk and signalling apparatus, cabinet switch and position transduser, wherein:
Signalling apparatus---form by a plurality of indicator lamps, can show whether the action of wing flap and flow deflector puts in place.
Cabinet switch---be two-way three source switchs, the folding and unfolding of direct control wing flap and the deflection of flow deflector.
Position transduser---the fabricate block for machinery and electric switch can be passed to the deflection state of wing flap folding and unfolding and flow deflector control desk and signalling apparatus thereof.
The utility model is because the combined control system of the same type of preparing between wing flap and flow deflector of employing one cover, only with a cabinet switch, just can carry out hormany operating to wing flap and flow deflector simultaneously, promptly when receiving wing flap, upward deflect flow deflector with certain rules; When putting wing flap, deflect down flow deflector with certain rule, the longitudinal moment that adopts this maneuvering system to overcome to handle respectively wing flap and flow deflector to cause is excessive, and the manipulation difficulty of when transition region is flown, bringing for aircraft.Longitudinal moment that it has not only made changes greatly and reduces, and make the operational motion of chaufeur become simplifications, convenience, guaranteed the safety that aircraft flies in transition region.
Description of drawings
Fig. 1 is that structure of the present utility model is formed block scheme;
Fig. 2 is that structure of the present utility model is formed principle schematic.
The specific embodiment
A kind of operating control of power-boosting ground effect aircraft for ground effect transition region, as shown in Figure 1 and Figure 2, comprising can be to wing flap and flow deflector hydraulic efficiency pressure system that drives simultaneously and the control circuit assembly that can handle, monitor and coordinate hydraulic work system, described hydraulic efficiency pressure system comprises hydraulic power source, cooperative control device and actuating unit, wherein:
Hydraulic power source---be used for providing pressure oil to actuating unit;
Cooperative control device---drive in the time of tunable control wing flap and flow deflector;
Actuating unit---can realize the execution of wing flap and flow deflector deflection action.
Hydraulic power source is the propulsion source of hydraulic efficiency pressure system.Mainly form by fuel tank, oil pump and voltage stabilizing, safety device.Described " voltage stabilizing, safety device " plays a part the deposit energy, voltage stabilizing and assurance system overpressure safety, mainly is made up of pressure accumulator, charge valve, cushion valve and safety valve.Wherein the air sac spherical accumulator is the device that is used for storing and discharging the hydraulic efficiency pressure system energy.Its main application is: can be used as auxiliary hydraulic pressure source, can guarantee the pressure oil delivery quality that once sails safe when the electric oil pump fault; Hydraulic efficiency pressure system is played pressurize, buffering, absorption hydraulic efficiency impact and reduces the charge valve of pressure pulsation effect, is to be used for to the gas filed valve of pressure accumulator air cavity; Cushion valve can reduce pressure pulsation and make the compression indicator indication accurately; Safety valve, when the pressure of hydraulic power source surpassed limit value, the automatic tapping step-down of meeting guaranteed that force value is in limited range.
Cooperative control device comprises wing flap, flow deflector conditioning unit, wing flap conditioning unit and flow deflector conditioning unit three partly.Described wing flap, flow deflector conditioning unit are used for coordinating wing flap and flow deflector deflection, make it from the off simultaneously, reach home simultaneously; Vice versa.It mainly is made up of reducing valve and solenoid directional control valve.Above-mentioned reducing valve, be the hydraulic power source force value to be reduced to actuating unit move needed operation pressure value, by regulating pressure relief value wing flap, the pressure of flow deflector deflection, flow are changed simultaneously, and, just can reach consistent on wing flap and the flow deflector deflection period by regulating the pressure oil decompression amount of wing flap and flow deflector.Above-mentioned solenoid directional control valve mainly is made up of valve body, electromagnet, spring and guiding valve.Principle of work is to change the flow direction of hydraulic oil by the diverse location of magnet control guiding valve.Described wing flap conditioning unit and flow deflector conditioning unit are respectively equipped with the flow-limiting valve of left and right wing flap of scalable driven in synchronism and left and right flow deflector.Above-mentioned wing flap conditioning unit and flow deflector conditioning unit can pass through the flow of flow-limiting valve adjustment pressure oil separately respectively, make left and right driven in synchronism.Be equipped with the hydraulic oil lock between above-mentioned wing flap, flow deflector conditioning unit and wing flap conditioning unit and the flow deflector conditioning unit.
Above-mentioned actuating unit comprises wing flap actuation mechanism, flow deflector actuation mechanism, described wing flap and flow deflector actuation mechanism are respectively equipped with left and right wing flap folding and unfolding pressurized strut and left and right flow deflector start folding and unfolding tube, are provided with the piston rod that can make wing flap, flow deflector deflection in the pressurized strut.When pressure oil flowed into the big chamber of pressurized strut, it was overhanging to promote piston rod, and wing flap and flow deflector are deflected down, and when pressure oil enters loculus, the piston rod withdrawal drives wing flap and flow deflector and packs up.
Above-mentioned control circuit assembly comprises control desk and signalling apparatus, cabinet switch and position transduser, and described maneuvering system mainly plays manipulation, monitoring and coordinative role.Wherein, signalling apparatus is made up of a plurality of indicator lamps, and whether indication wing flap and flow deflector put in place.Described cabinet switch is two-way three source switchs that are provided with retractable, neutral three gears, the direct control solenoid directional control valve, when cabinet switch places the position of " putting " be, solenoid directional control valve " is put " the end electromagnet and is got, supply pressure oil to the big chamber of pressurized strut, wing flap and flow deflector down inclined to one side (putting down).Handle when switch places the position of " receipts ", solenoid directional control valve " receipts " end electromagnet gets electric, " putting " end dead electricity, and for pressure oil, wing flap and flow deflector are packed up to pressurized strut (oil cylinder) loculus.When pack up to the position indicator lamp bright after, the cabinet switch handle is placed " neutrality " position.Position transduser also claims stop switch, is the fabricate block of machinery and electric switch, " puts " in order to experience wing flap and flow deflector, whether " receipts " put in place.When " putting " when putting in place, when experiencing signal, connects position transduser electric switch, and indicator lamp is bright on the control desk.When " receipts " when putting in place, when experiencing signal, connects position transduser electric switch, and indicator lamp is bright on the control desk, and makes solenoid directional control valve " receipts " end electromagnet dead electricity, and guiding valve work place meta, hydraulic oil lock be the pressurized strut locking, the maintenance retracted position.
Actual mechanical process of the present utility model is achieved in that at first doing wing flap and flow deflector handles dead work, opens electric hydraulic pump, electric hydraulic pump after fuel tank oil suction, supercharging by the pressure accumulator topping up of voltage supply pipeline to voltage stabilizing, safety device.When determining to put down wing flap and flow deflector, cabinet switch is placed the position of " putting ", pressure oil enters the big chamber of pressurized strut in wing flap actuation mechanism and the flow deflector actuation mechanism after by cooperative control device respectively, makes under overhanging promotion wing flap of piston rod and the flow deflector partially.Pressurized strut loculus hydraulic oil enters oil return line by cooperative control device, flows back to fuel tank.Regulate the coordination deflection of wing flap and flow deflector by the reducing valve in the cooperative control device; Wait by the flow-limiting valve in wing flap actuation mechanism and the flow deflector actuation mechanism and to regulate left and right wing flap driven in synchronism and left and right flow deflector driven in synchronism.When packing up wing flap and flow deflector, cabinet switch is placed the position of receipts, pressure oil enters the pressurized strut loculus in wing flap actuation mechanism and the flow deflector actuation mechanism after by cooperative control device respectively, makes that the piston rod withdrawal drives wing flap, flow deflector is packed up.The big chamber of pressurized strut hydraulic oil enters oil return line by cooperative control device, flows back to fuel tank.Because wing flap and flow deflector provide condition with overlapping hydraulic efficiency pressure system with one for both united control in the control system, flight test confirms, flap deflection 5 degree when taking off, flow deflector deflection 20 degree, pack up simultaneously in dried up back 15 seconds, can make ground effect vehicle successfully dried up and carry out the transition to cruising condition, whole process operation is easy, and flight attitude is stable.
Claims (2)
1, a kind of operating control of power-boosting ground effect aircraft for ground effect transition region, it is characterized in that comprising can be to wing flap and flow deflector hydraulic efficiency pressure system that drives simultaneously and the control circuit assembly that can handle, monitor and coordinate hydraulic work system, described hydraulic efficiency pressure system comprises hydraulic power source, cooperative control device and actuating unit, wherein:
Hydraulic power source---be used for providing pressure oil to actuating unit; Comprise fuel tank, electric hydraulic pump and voltage stabilizing, safety device, described voltage stabilizing, safety device are mainly formed by the oil line pipe serial connection by pressure accumulator, charge valve, cushion valve and safety valve, and wherein above-mentioned pressure accumulator is the air sac spherical accumulator;
Cooperative control device---drive in the time of tunable control wing flap and flow deflector; Comprise wing flap, flow deflector conditioning unit, wing flap conditioning unit and flow deflector conditioning unit, wherein:
Wing flap, flow deflector conditioning unit are made up of reducing valve and solenoid directional control valve, and an end of described reducing valve links to each other with the hydraulic power source delivery conduit, and the other end and solenoid directional control valve join;
Wing flap conditioning unit and flow deflector conditioning unit are respectively equipped with the flow-limiting valve that scalable is driven left and right wing flap and left and right flow deflector synchronously, are respectively equipped with the hydraulic oil lock between above-mentioned wing flap, flow deflector conditioning unit and wing flap conditioning unit and flow deflector conditioning unit;
Actuating unit---can realize the execution of wing flap and flow deflector deflection action; Comprise wing flap actuation mechanism, flow deflector actuation mechanism, described wing flap and flow deflector actuation mechanism are respectively equipped with left and right wing flap folding and unfolding pressurized strut and left and right flow deflector folding and unfolding pressurized strut, are provided with to drive the piston rod that connects mutually with left and right wing flap, left and right flow deflector respectively in pressurized strut.
2, the operating control of power-boosting ground effect aircraft for ground effect transition region according to claim 1 is characterized in that above-mentioned control circuit assembly comprises control desk and signalling apparatus, cabinet switch and position transduser, wherein:
Signalling apparatus---form by a plurality of indicator lamps, can show whether the action of wing flap and flow deflector puts in place;
Cabinet switch---be two-way three source switchs, the folding and unfolding of direct control wing flap and the deflection of flow deflector,
Position transduser---the fabricate block for machinery and electric switch can be passed to the deflection state of wing flap folding and unfolding and flow deflector control desk and signalling apparatus thereof.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 02271734 CN2574996Y (en) | 2002-07-11 | 2002-07-11 | Airport air navigation aiding lamp whole journey fault locating device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 02271734 CN2574996Y (en) | 2002-07-11 | 2002-07-11 | Airport air navigation aiding lamp whole journey fault locating device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2574996Y true CN2574996Y (en) | 2003-09-24 |
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ID=33736534
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 02271734 Expired - Lifetime CN2574996Y (en) | 2002-07-11 | 2002-07-11 | Airport air navigation aiding lamp whole journey fault locating device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2574996Y (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102015445A (en) * | 2008-04-24 | 2011-04-13 | 空中客车营运有限公司 | Lateral coupling device for holding and guiding at least one aerodynamic body in relation to the main wing of an aircraft, wing and aircraft comprising the same |
-
2002
- 2002-07-11 CN CN 02271734 patent/CN2574996Y/en not_active Expired - Lifetime
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102015445A (en) * | 2008-04-24 | 2011-04-13 | 空中客车营运有限公司 | Lateral coupling device for holding and guiding at least one aerodynamic body in relation to the main wing of an aircraft, wing and aircraft comprising the same |
| US8517315B2 (en) | 2008-04-24 | 2013-08-27 | Airbus Operations Gmbh | Lateral coupling device for holding and guiding at least one aerodynamic body relative to the main wing of an aircraft, airfoil and aircraft with such a lateral coupling device |
| CN102015445B (en) * | 2008-04-24 | 2014-12-10 | 空中客车营运有限公司 | Lateral coupling device for holding and guiding at least one aerodynamic body in relation to the main wing of an aircraft, wing and aircraft comprising the same |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Effective date of abandoning: 20050914 |
|
| C25 | Abandonment of patent right or utility model to avoid double patenting |