CN104477378A - Aircraft longitudinal maneuvering limit limiting method and device thereof - Google Patents
Aircraft longitudinal maneuvering limit limiting method and device thereof Download PDFInfo
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- CN104477378A CN104477378A CN201410664019.6A CN201410664019A CN104477378A CN 104477378 A CN104477378 A CN 104477378A CN 201410664019 A CN201410664019 A CN 201410664019A CN 104477378 A CN104477378 A CN 104477378A
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Abstract
The invention belongs to an aircraft control design technology, and relates to an aircraft longitudinal maneuvering limit limiting method and a device thereof. The limit limiting device comprises a steering engine (101), a spring pull rod (102) and a sealing outlet (103). According to the aircraft longitudinal maneuvering limit limiting method and the device thereof provided by the invention, an obvious hint can be given to the body of an aviator when an aircraft achieves a limiting condition; the fact that the aircraft achieves a limit state is hinted, so that the aviator needs to take care maneuvering motion; simultaneously, a part of super-control capability is also given to the aviator; the aircraft longitudinal maneuvering limit limiting method and the device thereof are used for emergent maneuvering under emergent conditions; and in addition, compared with simple use of software limit, the aircraft longitudinal maneuvering limit limiting method and device thereof are more intuitionistic and effective.
Description
Technical field
The invention belongs to flight control design case technology, relate to a kind of aircraft fore-and-aft control limit method for limiting and device thereof.
Background technology
The limit angle of attack and the extreme overload restriction of conventional fax aircraft longitudinal direction use software restriction usually.From flight quality angle, software is limited under some complex situations and can not points out intuitively to aviator one: aircraft has reached capacity state.In large ram compression situation, the normal g-load that can promote rapidly aircraft handled by too fast and too much longitudinal tie, can exceed the intensity restriction of aircraft, thus cause aircraft stall under serious conditions.
Summary of the invention
The technical problem to be solved in the present invention is: provide a kind of when aircraft angle of attack or overload transfinite to the aircraft fore-and-aft control limit method for limiting of obviously prompting on aviator's health.
Technical scheme of the present invention is:
A kind of aircraft fore-and-aft control limit restraint device, is characterized by: described limit restraint device comprises steering wheel 101, spring pull bar 102, sealing outlet 103;
Described steering wheel 101 comprises hydraulic actuation cartridge module I, electromechanical transducer II, hydraulic amplifier III; The execution annex that described steering wheel 101 limits as the limit, receives the control command motion of flight control computer;
Described hydraulic actuation cartridge module I comprises oil filter 201, micro-switch 203, feedback transducer 202, is communicated with valve 207; The displacement of the signal that described feedback transducer 202 sends and steering wheel rocking arm 206 is proportional; Two micro-switchs 203 send signal to the end position of steering wheel rocking arm 206; Described oil filter 201 purification enters the operating fluid of limit restriction steering wheel; Described connection valve 207 is communicated with one group of columniform chamber when not having working fluid pressure, again they are separated when there is working fluid pressure; Described hydraulic actuation cartridge module I is the HM Hydraulic Motor in single chamber, and the energy that operating fluid can be flowed is moved by promotion piston rod and changes mechanical energy into;
Described hydraulic amplifier III carrys out operating hydraulically operated motor by operating fluid and amplifies the power handling electric signal simultaneously, and it is a hydraulic bridge, and wherein two brachium pontis are constant liquid resistances, and the liquid resistance of another two brachium pontis can change; A diagonal line of hydraulic bridge connects hydraulic power source, and carrying out oily circuit is pipeline E, and oil return circuit is pipeline D; And be load at another diagonal line of hydraulic bridge, oil distributor is pipeline F1 and pipeline F2; Throttle valve A 209, flow regulating valve B214 are used to provide constant liquid resistance, are used to provide variable liquid resistance with the nozzle A211 of the baffle plate 212 of electromechanical transducer II, nozzle B 213, and valve 210 is used as to reduce and keep working fluid pressure constant;
Electromechanical transducer II is used as the transformation controlling electric signal, and the transformation of electric signal is proportional with the displacement of the baffle plate of hydraulic amplifier III;
Steering wheel 101 works in such a way: when connecting solenoid valve 215, and operating fluid flows into hydraulic amplifier III along oil feed line B through oil filter 201 under hydraulic system pressure, flows to the end being communicated with valve 207 simultaneously; Under pressure, the distributing valve being communicated with valve 207 moves and the epitrochoidal chamber of hydraulic actuation cartridge module I is separated; When not controlling electric signal, the end face of nozzle A211, nozzle B 213 is equal with the gap between baffle plate 212, and hydraulic bridge keeps balance; The both ends of the surface pressure of distributing valve 208 is equal; Distributing valve 208 is positioned at midway location, does not produce the distribution of power fluid; When the coil providing manipulation electric signal to electromechanical transducer II, baffle plate 212 deflects with regard to destroying hydraulic bridge steady by midway location; In pipeline F2, working liquid pressure declines, and in pipeline F1, pressure raises, and occurs pressure reduction, cause distributing valve 208 to move to the side that pressure is little at distributing valve two end, and opens operating fluid entrance by oil feed line B and enter pipeline C; Operating fluid enters hydraulic oil-returning pipeline and pipeline D by pipeline A; The flow of operating fluid and being in proportion of control electric signal; Operating fluid enters hydraulic actuation cartridge module I along pipeline C under stress, and mobile piston 204 also drives steering wheel rocking arm 206 to move together; When opposite polarity signal arrives, distributing valve 208 moves in the opposite direction, and the contrary chamber of hydraulic actuation cartridge module I is communicated with oil feed line B by pipeline A, and therefore steering wheel rocking arm 206 just moves to another direction; Operating fluid flows into oil return line and pipeline D by pipeline C; Sensor 202 is connected with steering wheel rocking arm 206 by piston 204, along with the change of steering wheel rocking arm 206 position, feedback transducer 202 changes the angle of rotating, and at this moment feedback transducer 202 sends position signal to flight control computer, and this signal corresponds to the stroke that steering wheel rocking arm 206 leaves center position; When steering wheel rocking arm 206 is greater than forced stroke to the distance of this face or that face movement, micro-switch 203 is switched on; When removing manipulation electric signal, all parts turn back to reference position; When not having charge oil pressure or solenoid valve 215 binding post do not have voltage, steering wheel rocking arm 206 is stabilized to center position under the effect of spring 205;
Spring pull bar 102, as the motion of the drive disk assembly transmission steering wheel of steering wheel 101, when there is the angle of attack and overload transfinites, provides the additional manipulation power of jociey stick;
The rotating shaft 403 of sealing outlet 103 is arranged on bearing A405, bearing B406 and bearing 404, and rotating shaft is provided with rocking arm A401, rocking arm B407, rocking arm C414;
It is interior and connected with the pull bar A402 being connected jociey stick that rocking arm A401 is arranged in passenger cabin; Under rocking arm B407, rocking arm C414 are arranged in cockpit floor, rocking arm B407 is connected with sensor 409 with control feel simulator 410 respectively;
Rocking arm C414 is connected with steering wheel 101 by spring pull bar 102;
Rocking arm B407 and rotating shaft 403 are rigidly connected, and with adjustable debooster 412 on the lug of rocking arm B407, when aircraft enters the critical angle of attack and overload, by adjustable debooster 412, non-adjustable debooster 413, ensures on jociey stick, increase additional stick force;
Bearing 404 is arranged on cockpit floor by bolt seal.
Use an aircraft fore-and-aft control limit method for limiting for above-mentioned limit restraint device, it is characterized by described method and comprise:
1) when not reaching limiting condition, flight control computer calculates the command signal of steering wheel 101 according to the displacement signal of jociey stick pitch orientation, and the steering wheel rocking arm 206 controlling steering wheel 101 follows the deflection of jociey stick; Jociey stick within the specific limits pull bar time, the setting gap between adjustable debooster 412 and non-adjustable debooster 413 is constant all the time, steering wheel 101 nonintervention handle;
2) when the angle of attack or pitch orientation overload are greater than limit value, steering wheel 101 stops following the tracks of jociey stick and moves, continue the gap that 1 ° 30 ' ~ 2 °, pull bar will be eliminated between adjustable debooster 412 and non-adjustable debooster 413, as now will pull bar be continued, the power of 150N ~ 190N need be applied more on normal operational power basis, thus aviator's aircraft angle of attack or overload can be pointed out to transfinite.
The invention has the beneficial effects as follows: the invention provides a kind of aircraft fore-and-aft control limit restraint device and method, can significantly imply by the health when aircraft reaches limiting condition to aviator, prompting aircraft has reached capacity state, note control action, also give the ability of aviator's part override simultaneously, for emergency control in case of emergency, with uses merely software limit compared with more intuitively with effective.
Accompanying drawing explanation
Fig. 1 is the fore-and-aft control limit restraint device composition schematic diagram in the present invention;
Fig. 2 is the steering wheel composition schematic diagram in the present invention;
Fig. 3 is the spring pull bar composition schematic diagram in the present invention;
Fig. 4 is the sealing outlet composition schematic diagram in the present invention;
Fig. 5 is the longitudinal limit restriction schematic diagram in the present invention;
Wherein, 101-steering wheel, 102-spring pull bar, 103-seals outlet, I-hydraulic actuation cartridge module, II-electromechanical transducer, III-hydraulic amplifier, the filter of 201-oil, 202-feedback transducer, 203-micro-switch, 204-piston, 205-spring, 206-steering wheel rocking arm, 207-is communicated with valve, 208-distributing valve, 209-throttle valve A, 210-valve, 211-nozzle A, 212-baffle plate, 213-nozzle B, 214-flow regulating valve B, 215-solenoid valve, 301-forked element, 302-safety key, 303-nut A, 304-portable bar, 305-check screw A, 306-check screw B, 307-check screw C, 308-sleeve, 309-check screw D, 310-spring cotter, 311-nut B, 312-lining A, 313-spring A, 314-lining B, 315-spring B, 316-cylindrical sleeves, 317-lining C, 318-spring C, 319-lining D, 320-covers, 321-check screw E, 322-obturages lining, 401-rocking arm A, 402-pull bar A, 403-rotating shaft, 404-bearing, 405-bearing A, 406-bearing B, 407-rocking arm B, 408-pull bar B, 409-sensor, 410-control feel simulator, the projection seat of 411-debooster, 412-is adjustable debooster, the non-adjustable debooster of 413-, 414-rocking arm C, 415-seal ring.
Detailed description of the invention
Below in conjunction with accompanying drawing, the specific embodiment of the present invention is described further.
See Fig. 1, a kind of aircraft fore-and-aft control limit restraint device, comprises steering wheel 101, spring pull bar 102, sealing outlet 103.
Participate in Fig. 2, the composition and working principle of steering wheel 101 is as follows:
(1) steering wheel 101
Steering wheel 101 comprises hydraulic actuation cartridge module I, electromechanical transducer II, hydraulic amplifier III; The execution annex that described steering wheel 101 limits as the limit, receives the control command motion of flight control computer.
Hydraulic actuation cartridge module I comprises oil filter 201, micro-switch 203, feedback transducer 202, is communicated with valve 207.
Feedback transducer 202 is for measuring the displacement of steering wheel rocking arm 206.
Two micro-switchs 203 send signal according to the end position of steering wheel rocking arm 206.
Oil filter 201 purification enters the operating fluid of limit restriction steering wheel.
Being communicated with valve 207 one group of columniform chamber is communicated with when not having working fluid pressure, again they being separated when there is working fluid pressure.
Hydraulic actuation cartridge module I is the HM Hydraulic Motor in single chamber, and the energy that operating fluid can be flowed is moved by promotion piston rod and changes mechanical energy into.
Hydraulic amplifier III carrys out operating hydraulically operated motor by operating fluid and amplifies the power handling electric signal simultaneously, and it is a hydraulic bridge, and wherein two brachium pontis are constant liquid resistances, and the liquid resistance of another two brachium pontis can change.A diagonal line of hydraulic bridge connects hydraulic power source, and carrying out oily circuit is pipeline E, and oil return circuit is pipeline D, and is load at another diagonal line of hydraulic bridge, and oil distributor is pipeline F1 and pipeline F2.Throttle valve A 209, flow regulating valve B214 are used to provide constant liquid resistance, are used to provide variable liquid resistance with the nozzle A211 of the baffle plate 212 of electromechanical transducer II, nozzle B 213, and valve 210 is used as to reduce and keep working fluid pressure constant.
Electromechanical transducer II is used as the transformation controlling electric signal, and the transformation of electric signal is proportional with the displacement of the baffle plate of hydraulic amplifier III;
Electromechanical transducer II is used as the transformation controlling electric signal, and the transformation of electric signal is proportional with the displacement of the baffle plate of nozzle-baffle type hydraulic amplifier.
(2) principle of work of steering wheel 101
When connecting solenoid valve 215, operating fluid flows into hydraulic amplifier III along oil feed line B through oil filter 201 under hydraulic system pressure, flows to the end being communicated with valve 207 simultaneously.Under pressure, the distributing valve being communicated with valve 207 moves and the epitrochoidal chamber of hydraulic actuation cartridge module I is separated.When not controlling electric signal, the end face of nozzle A211, nozzle B 213 is equal with the gap between baffle plate 212, and hydraulic bridge keeps balance, and the both ends of the surface pressure of distributing valve 208 is equal, and distributing valve 208 is positioned at midway location, does not produce the distribution of power fluid.When the coil providing manipulation electric signal to electromechanical transducer II, baffle plate 212 deflects with regard to destroying hydraulic bridge steady by midway location, in pipeline F2, working liquid pressure declines, and pressure raises in pipeline F1, pressure reduction is there is at distributing valve two end, cause distributing valve 208 to move to the side that pressure is little, and open operating fluid entrance and enter pipeline C by oil feed line B, operating fluid enters hydraulic oil-returning pipeline and pipeline D by pipeline A.The flow of operating fluid and being in proportion of control electric signal.Operating fluid enters hydraulic actuation cartridge module I along pipeline C under stress, and mobile piston 204 also drives steering wheel rocking arm 206 to move together.When opposite polarity signal arrives, distributing valve 208 moves in the opposite direction, the contrary chamber of hydraulic actuation cartridge module I is communicated with oil feed line B by pipeline A, and therefore steering wheel rocking arm 206 just moves to another direction, and operating fluid flows into oil return line and pipeline D by pipeline C.Sensor 202 is connected with steering wheel rocking arm 206 by piston 204, along with the change of steering wheel rocking arm 206 position, feedback transducer 202 changes the angle of rotating, and at this moment feedback transducer 202 sends position signal to flight control computer, and this signal corresponds to the stroke that steering wheel rocking arm 206 leaves center position.When steering wheel rocking arm 206 is greater than forced stroke to the distance of this face or that face movement, micro-switch 203 is switched on.When removing manipulation electric signal, all parts turn back to reference position.When not having charge oil pressure or solenoid valve 215 binding post do not have voltage, steering wheel rocking arm 206 is stabilized to center position under the effect of spring 205.
See Fig. 3, as shown in the figure, its drive disk assembly as steering wheel transmits the motion of steering wheel to the composition of spring pull bar 102, when there is the angle of attack and overload transfinites, provides the additional manipulation power of jociey stick.
See Fig. 4, the rotating shaft 403 of sealing outlet 103 is arranged on bearing A405, bearing B406 and bearing 404, and rotating shaft is provided with rocking arm A401, rocking arm B407, rocking arm C414.
It is interior and connected with the pull bar A402 being connected jociey stick that rocking arm A401 is arranged in passenger cabin; Under rocking arm B407, rocking arm C414 are arranged in cockpit floor, rocking arm B407 is connected with sensor 409 with control feel simulator 410 respectively.
Rocking arm C414 is connected with steering wheel 101 by spring pull bar 102.
Rocking arm B407 and rotating shaft 403 are rigidly connected, and with adjustable debooster 412 on the lug of rocking arm B407, when aircraft enters the critical angle of attack and overload, by adjustable debooster 412, non-adjustable debooster 413, ensures on jociey stick, increase additional stick force;
Bearing 404 is arranged on cockpit floor by bolt seal.
Bearing 4 is arranged on cockpit floor by bolt seal.
See Fig. 5, when not reaching limiting condition, flight control computer calculates the command signal of steering wheel 101 according to the displacement signal of jociey stick pitch orientation, and the steering wheel rocking arm 206 controlling steering wheel 101 follows the deflection of jociey stick.Jociey stick within the specific limits pull bar time, the setting gap between adjustable debooster 412 and non-adjustable debooster 413 is constant all the time, steering wheel 101 nonintervention handle.When the angle of attack or pitch orientation overload are greater than limit value, steering wheel 101 stops following the tracks of jociey stick and moves, continue the gap that 1 ° 30 ' ~ 2 °, pull bar will be eliminated between adjustable debooster 412 and non-adjustable debooster 413, as now will pull bar be continued, 150N ~ 190N kgf need be applied more on normal operational power basis, thus aviator's aircraft angle of attack or overload can be pointed out to transfinite.
Claims (2)
1. an aircraft fore-and-aft control limit restraint device, is characterized by: described limit restraint device comprises steering wheel (101), spring pull bar (102), sealing outlet (103);
Described steering wheel (101) comprises hydraulic actuation cartridge module I, electromechanical transducer II, hydraulic amplifier III; The execution annex that described steering wheel (101) limits as the limit, receives the control command motion of flight control computer;
Described hydraulic actuation cartridge module I comprises oil filter (201), micro-switch (203), feedback transducer (202), is communicated with valve (207); The displacement of the signal that described feedback transducer (202) sends and steering wheel rocking arm (206) is proportional; Two micro-switchs (203) send signal to the end position of steering wheel rocking arm (206); Described oil filter (201) purification enters the operating fluid of limit restriction steering wheel; Described connection valve (207) is communicated with one group of columniform chamber when not having working fluid pressure, again they are separated when there is working fluid pressure; Described hydraulic actuation cartridge module I is the HM Hydraulic Motor in single chamber, and the energy that operating fluid can be flowed is moved by promotion piston rod and changes mechanical energy into;
Described hydraulic amplifier III carrys out operating hydraulically operated motor by operating fluid and amplifies the power handling electric signal simultaneously, and it is a hydraulic bridge, and wherein two brachium pontis are constant liquid resistances, and the liquid resistance of another two brachium pontis can change; A diagonal line of hydraulic bridge connects hydraulic power source, and carrying out oily circuit is pipeline E, and oil return circuit is pipeline D; And be load at another diagonal line of hydraulic bridge, oil distributor is pipeline F1 and pipeline F2; Throttle valve A (209), flow regulating valve B (214) are used to provide constant liquid resistance, be used to provide variable liquid resistance with the nozzle A (211) of the baffle plate (212) of electromechanical transducer II, nozzle B (213), valve (210) is used as to reduce and keep working fluid pressure constant;
Electromechanical transducer II is used as the transformation controlling electric signal, and the transformation of electric signal is proportional with the displacement of the baffle plate of hydraulic amplifier III;
Steering wheel (101) works in such a way: when connecting solenoid valve (215), operating fluid flows into hydraulic amplifier III along oil feed line B through oil filter (201) under hydraulic system pressure, flows to the end being communicated with valve (207) simultaneously; Under pressure, the distributing valve being communicated with valve (207) moves and the epitrochoidal chamber of hydraulic actuation cartridge module I is separated; When not controlling electric signal, the end face of nozzle A (211), nozzle B (213) is equal with the gap between baffle plate (212), and hydraulic bridge keeps balance; The both ends of the surface pressure of distributing valve (208) is equal; Distributing valve (208) is positioned at midway location, does not produce the distribution of power fluid; When the coil providing manipulation electric signal to electromechanical transducer II, baffle plate (212) deflects with regard to destroying hydraulic bridge steady by midway location; In pipeline F (2), working liquid pressure declines, and pressure raises in pipeline F (1), there is pressure reduction at distributing valve two end, cause distributing valve (208) to move to the side that pressure is little, and open operating fluid entrance and enter pipeline C by oil feed line B; Operating fluid enters hydraulic oil-returning pipeline and pipeline D by pipeline A; The flow of operating fluid and being in proportion of control electric signal; Operating fluid enters hydraulic actuation cartridge module I along pipeline C under stress, and mobile piston (204) also drives steering wheel rocking arm (206) to move together; When opposite polarity signal arrives, distributing valve (208) moves in the opposite direction, and the contrary chamber of hydraulic actuation cartridge module I is communicated with oil feed line B by pipeline A, and therefore steering wheel rocking arm (206) just moves to another direction; Operating fluid flows into oil return line and pipeline D by pipeline C; Sensor (202) is connected with steering wheel rocking arm (206) by piston (204), along with the change of steering wheel rocking arm (206) position, feedback transducer (202) changes the angle of rotating, at this moment feedback transducer (202) sends position signal to flight control computer, and this signal corresponds to the stroke that steering wheel rocking arm (206) leaves center position; When steering wheel rocking arm (206) is greater than forced stroke to the distance of this face or that face movement, micro-switch (203) is switched on; When removing manipulation electric signal, all parts turn back to reference position; When not having charge oil pressure or solenoid valve (215) binding post do not have voltage, steering wheel rocking arm (206) is stabilized to center position under the effect of spring (205);
Spring pull bar (102), as the motion of the drive disk assembly transmission steering wheel of steering wheel (101), when there is the angle of attack and overload transfinites, provides the additional manipulation power of jociey stick;
The rotating shaft (403) of sealing outlet (103) is arranged on bearing A (405), bearing B (406) and bearing (404), and rotating shaft is provided with rocking arm A (401), rocking arm B (407), rocking arm C (414);
It is interior and connected with the pull bar A (402) being connected jociey stick that rocking arm A (401) is arranged in passenger cabin; Under rocking arm B (407), rocking arm C (414) are arranged in cockpit floor, rocking arm B (407) is connected with sensor (409) with control feel simulator (410) respectively;
Rocking arm C (414) is connected by spring pull bar (102) same to steering wheel (101);
Rocking arm B (407) and rotating shaft (403) are rigidly connected, with adjustable debooster (412) on the lug of rocking arm B (407), when aircraft enters the critical angle of attack and overload, by adjustable debooster (412), non-adjustable debooster (413), ensure on jociey stick, increase additional stick force;
Bearing (404) is arranged on cockpit floor by bolt seal.
2. use an aircraft fore-and-aft control limit method for limiting for limit restraint device described in claim 1, it is characterized by described method and comprise:
2.1) when not reaching limiting condition, flight control computer calculates the command signal of steering wheel (101) according to the displacement signal of jociey stick pitch orientation, and the steering wheel rocking arm (206) controlling steering wheel (101) follows the deflection of jociey stick; Jociey stick within the specific limits pull bar time, the setting gap between adjustable debooster (412) and non-adjustable debooster (413) is constant all the time, steering wheel (101) nonintervention handle;
2.2) when the angle of attack or pitch orientation overload are greater than limit value, steering wheel (101) stops following the tracks of jociey stick and moves, continue pull bar 1 ° 30 ' ~ 2 ° gaps will eliminated between adjustable debooster (412) and non-adjustable debooster (413), as now will pull bar be continued, the power of 150N ~ 190N need be applied more on normal operational power basis, thus aviator's aircraft angle of attack or overload can be pointed out to transfinite.
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| CN201410664019.6A CN104477378B (en) | 2014-11-19 | 2014-11-19 | A kind of aircraft fore-and-aft control limit method for limiting and its device |
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| CN201410664019.6A CN104477378B (en) | 2014-11-19 | 2014-11-19 | A kind of aircraft fore-and-aft control limit method for limiting and its device |
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