CN106703995B - A kind of inlet lip distressed structure and inlet lip distressed structure control method - Google Patents
A kind of inlet lip distressed structure and inlet lip distressed structure control method Download PDFInfo
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- CN106703995B CN106703995B CN201611050446.0A CN201611050446A CN106703995B CN 106703995 B CN106703995 B CN 106703995B CN 201611050446 A CN201611050446 A CN 201611050446A CN 106703995 B CN106703995 B CN 106703995B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/057—Control or regulation
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
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- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a kind of inlet lip distressed structure and inlet lip distressed structure control method.The inlet lip distressed structure includes main bearing structure, covering, lip configuration, temperature sensor, multiple strain transducers, temperature-adjusting device and lip configuration drive device；The main bearing structure is manufactured using memory alloy material, and is arranged in the closed cavity of covering formation；The closed cavity is provided with air inlet and gas outlet；The temperature-adjusting device is connected with the air inlet of the closed cavity；The temperature sensor is arranged in the main bearing structure；The strain transducer is arranged on the inner surface and main bearing structure of covering；The lip configuration drive device is arranged in the main bearing structure.The inlet lip distressed structure control method mainly realizes control using above-mentioned inlet lip distressed structure.It is an advantage of the invention that：The lip of air intake duct can change shape repeatedly according to practical flight speed within the specific limits.
Description
Technical field
The present invention relates to aeronautic structure design field, and in particular to a kind of inlet lip distressed structure and air intake duct
Lip distressed structure control method.
Background technology
It is ultrasonic aircraft for maximum flight M numbers, the matching problem of air inlet/engine is one intractable all the time
Problem.Aircraft is from static to takeoff condition, and speed of incoming flow is by zero gradually increase, because speed of incoming flow is very low, into air intake duct
Air-flow can be sucked into from surrounding environment, separate air intake duct interior air-flow, and air inlet lip is thinner, this air-flow separation
It is more serious, cause inlet throat to block, increase engine intake flow distortion, pitot loss increase, thrust loss increase,
The increase of aircraft ground run distance.
The content of the invention
It is an object of the invention to provide a kind of inlet lip distressed structure and inlet lip distressed structure control method,
To solve the problems, such as or at least mitigate at least one in the presence of background technology.
The technical scheme is that：A kind of inlet lip distressed structure is provided, includes main bearing structure, covering and lip
Edge structure, one end of the main bearing structure are fixed on cantilever support beam, and the other end connects the lip configuration, the covering
It is coated on outside the lip configuration；The inlet lip distressed structure also comprising temperature sensor, multiple strain transducers,
Temperature-adjusting device and lip configuration drive device；
The main bearing structure is manufactured using memory alloy material, and is arranged in the closed cavity that the covering is formed；
The closed cavity is provided with air inlet and gas outlet；The temperature-adjusting device and the air inlet of the closed cavity
Mouth connection, for adjusting the temperature in the closed cavity；
The temperature sensor is arranged in the main bearing structure；
The strain transducer is arranged on the inner surface and the main bearing structure of the covering；
The lip configuration drive device is arranged in the main bearing structure, for driving the lip configuration.
Preferably, the lip configuration includes fixed part and adjustment portion, one end of the fixed part and the adjustment portion
One end is fixedly connected, and the fixed part is fixedly connected with the main bearing structure；The one side of the adjustment portion and the covering
Inner surface fitting, for supporting the covering, in the adjustment portion on the another side relative with the inner surface of the covering
It is provided with strain transducer.
Preferably, the lip configuration drive device includes the first drive mechanism, pulley and flexible rope；Described first drives
Motivation structure is fixed in the main bearing structure, the pulley be arranged on the lip configuration and first drive mechanism it
Between；The flexible rope bypasses the pulley, and one end is connected with first drive mechanism, and the other end and the adjustment portion are remote
One end connection of fixed part.
Preferably, the inlet lip distressed structure also includes flow sensor and pressure transducer, and the flow passes
Sensor and pressure transducer are arranged in the main bearing structure；The temperature-adjusting device includes cold air tank and hot gas tank, institute
The air inlet that cold air tank is stated with the hot gas tank difference closed cavity connects.
Preferably, the cold air tank is used in gas tank with being respectively arranged with booster pump, the booster pump on hot gas tank
Gas is sent into the closed cavity.
Preferably, the inlet lip distressed structure is also comprising dimension shape cable wire, one end connection institute of the dimension shape cable wire
The inwall of covering is stated, the other end connects the main bearing structure.
The present invention has been also provided to a kind of inlet lip distressed structure control method, using air intake duct lip as described above
Mouth distressed structure, is comprised the steps of：
Step 1: lip shape control law of the design aircraft under different flying speeds is required according to aircraft inlet engine compatibility,
The inlet engine compatibility refers to the matching of air intake duct flow and engine；
Step 2: according to the deformation of main bearing structure and the corresponding relation of temperature that are made up of memorial alloy and lip shape
The temperature control rule of main bearing structure described in shape design of control law, and lip configuration is controlled according to lip shape design of control law
The first drive control rule of first drive mechanism, and control the second drive control rule of the second servo-actuated drive mechanism of covering；
Step 3: obtaining current flight state, determine that lip shape control law corresponding to current flight state inputs, and according to
The input of secondary temperature control law, the input of the first drive control rule and the input of the second drive control rule；
Step 4: the input restrained according to temperature control controls the ratio of the cold air and hot gas in the closed cavity being made up of covering
Example output, meanwhile, the shape that input control antelabium is restrained according to antelabium drive control exports.
In above-mentioned inlet lip distressed structure control method, it is preferable that the step 3 also includes obtaining current fly
Inlet lip shape under row state, and it is supplied to the first drive mechanism as data feedback.
In above-mentioned inlet lip distressed structure control method, it is preferable that the step 3 also includes obtaining current fly
The temperature and pressure in closed cavity being made up of under row state covering, and give booster pump controlling organization as data feedback.
In above-mentioned inlet lip distressed structure control method, it is preferable that in the step 4, by cold air or hot gas
Before being transported in the closed cavity, further comprise with the hot gas mixing outside the closed cavity cold air equal
It is even to certain temperature.
The advantage of the invention is that：The invention provides a kind of inlet lip distressed structure and inlet lip deformation knot
Structure control method, the lip of air intake duct can change shape repeatedly within the specific limits, suitable according to practical flight speed, setting
Inlet lip, solve the problems, such as that lip configuration is unadjustable in the prior art, make air intake duct under different flight state
All there is optimal aeroperformance and inlet engine compatibility characteristic.
Brief description of the drawings
Fig. 1 is the inlet lip distressed structure schematic diagram of one embodiment of the invention.
Fig. 2 is the lip configuration schematic diagram in the inlet lip distressed structure shown in Fig. 1.
Fig. 3 is the thermostatic schematic diagram in the inlet lip distressed structure shown in Fig. 1.
Wherein, the main bearing structures of 1-, 2- coverings, 3- lip configurations, 31- fixed parts, 32- adjustment portions, 4- cantilever support beams,
The drive mechanisms of 5- first, 6- pulleys, 7- flexible ropes, 8- temperature sensors, 9- strain transducers, 10- gas outlets, 11- pressure
Sensor, 12- flow sensors, 13- cold air tanks, 14- hot gas tanks, 15- dimension shape cable wires.
Embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
Part of the embodiment, rather than whole embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to uses
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.Under
Embodiments of the invention are described in detail with reference to accompanying drawing for face.
In the description of the invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outer " is based on accompanying drawing institutes
The orientation or position relationship shown, it is for only for ease of the description present invention and simplifies description, rather than instruction or the dress for implying meaning
Put or element there must be specific orientation, with specific azimuth configuration and operation, therefore it is not intended that the present invention is protected
The limitation of scope.
Supersonic inlet is in order to meet flow matches with engine, it is necessary to be done using air intake duct lower lip is movable
Method.At low speeds, flow separation can be reduced, reduce flow distortion, improve motor power.Movable antelabium also has in addition
One function is that the capture flow of Fighter Inlet is adjusted in the case of supersonic flight, changes supersonic speed throat area, carries
Height enters/send out matching performance.
Inlet lip deformable structure can change shape in the larger context.Aircraft in flight course, it is necessary to
Shape above and below real-time perception lip, and lip configuration is controlled according to current flying speed, so as to increase or reduce
The air inlet open area of air intake duct, to adapt to the traffic demand of engine and inlet engine compatibility performance.
As shown in Figure 1 to Figure 3, a kind of inlet lip distressed structure, main bearing structure 1, covering 2 and lip configuration are included
3.One end of main bearing structure 1 is fixed on cantilever support beam 4, and other end connection lip configuration 3, covering 2 is coated on antelabium knot
Outside structure 3.The inlet lip distressed structure is also comprising temperature sensor 8, multiple strain transducers 9, temperature-adjusting device
And lip configuration drive device.
Main bearing structure 1 is manufactured using memory alloy material, and is arranged in the closed cavity of the formation of covering 2.In this reality
Apply in example, the memorial alloy is the marmem with double-pass memory effect, and memory can be controlled by changing temperature
The shape of alloy.
The closed cavity is provided with air inlet and gas outlet 10；The temperature-adjusting device enters with the closed cavity
Gas port connects, for adjusting the temperature in the closed cavity.
Temperature sensor 8 is arranged in main bearing structure 1, for detecting the temperature of main bearing structure 1.In the present embodiment
In, temperature sensor 8 is provided with multiple, the advantage is that the multi-point temp that can be detected in main bearing structure 1, it is ensured that warm everywhere
Degree is uniform.
Strain transducer 9 is arranged on the inner surface and main bearing structure 1 of covering 2, for detecting deformation and the master of covering 2
The deformation of bearing structure 1.In the present embodiment, strain transducer 9 is respectively provided with the inner surface of covering 2 and main bearing structure 1
There is multiple, the strain of convenient detection everywhere.
The lip configuration drive device is arranged in main bearing structure 1, for driving the lip configuration 3.
The inlet lip distressed structure of the present invention is by controlling the temperature in closed cavity, thus it is possible to vary main bearing structure
1 shape, the deformation of inlet lip is realized, to adapt to the different flying speeds of aircraft, make air intake duct in different flight state
Under all there is optimal aeroperformance and inlet engine compatibility characteristic.
In the present embodiment, lip configuration 3 includes fixed part 31 and adjustment portion 32, one end and the adjustment portion 32 of fixed part 31
One end be fixedly connected, fixed part 31 is fixedly connected with main bearing structure 1.The one side of adjustment portion 32 and the inner surface of covering 2
Fitting, for supporting covering 2, strain transducer is provided with the another side relative with the inner surface of covering 2 in adjustment portion 32
9, strain transducer 9 is used for the strain for detecting adjustment portion 32.As shown in Fig. 2 fixed part 31 has angle with the shape of adjustment portion 32.
In the present embodiment, the lip configuration drive device includes the first drive mechanism 5, pulley 6 and flexible rope 7；
First drive mechanism 5 is fixed in main bearing structure 1, and pulley 6 is arranged between the drive mechanism 5 of lip configuration 3 and first；It is flexible
Rope 7 bypasses pulley 6, and one end is connected with the first drive mechanism 5, and the other end connects with the one end of adjustment portion 32 away from fixed part 31
Connect.The rotating engine flexible rope 7 of first drive mechanism 5, flexible rope 7 pull adjustment portion 32, and adjustment portion 32 is towards fixed part 31
Deformation, the angle between adjustment portion 32 and fixed part 31 diminish, and the shape of lip configuration 3 changes.
In the present embodiment, the inlet lip distressed structure also includes flow sensor 12 and pressure transducer 11,
The flow sensor 12 and pressure transducer 11 are arranged in main bearing structure 1；The temperature-adjusting device includes cold air tank
13 with hot gas tank 14, and the air inlet that cold air tank 13 distinguishes the closed cavity with hot gas tank 14 connects.Cold air tank 13 is used for for envelope
Closing and cold air is passed through in cavity, hot gas tank 14 is used for be passed through hot gas in closed cavity, by controlling the intake of cold air and hot gas,
The temperature in closed cavity can be adjusted, and then adjusts the shape of main bearing structure 1.Flow sensor 12 is used to detect closing sky
The gas flow of intracavitary, pressure transducer 11 is used to detect the pressure in closed cavity, by changing the pressure in closed cavity,
The shape of covering 2 can be changed.
In the present embodiment, cold air tank 13 is used for gas with being respectively arranged with booster pump, the booster pump on hot gas tank 14
Gas in tank is sent into the closed cavity.
In the present embodiment, the inlet lip distressed structure is also comprising dimension shape cable wire 15, one end of dimension shape cable wire 15
The inwall of covering 2 is connected, the other end connects main bearing structure 1.It is scalable cable wire to tie up shape cable wire 15, when the pressure in closed cavity
During strong increase, covering 2 moves out, stretching dimension shape cable wire 15；When the pressure in closed cavity reduces, covering 2 is withdrawn, and ties up shape
Cable wire 15 accordingly bounces back.
Present invention also offers a kind of inlet lip distressed structure control method, using inlet lip as described above
Distressed structure, comprise the steps of：
Step 1: lip shape control law of the design aircraft under different flying speeds is required according to aircraft inlet engine compatibility,
The inlet engine compatibility refers to the matching of air intake duct flow and engine.
Specifically, according to inlet engine compatibility characteristic, design inlet lip is under different flying speeds during three kinds of discrete states
Shape, determine three kinds of states of main bearing structure 1, covering 2 and lip configuration 3.As shown in table 1, three kinds of inlet lip
State refers to the angle of lip configuration, L for upper state, intermediateness and lower inclined state, wherein α partiallyijThe drawing of cable wire is driven for antelabium
The amount of stretching, and have T1>T2>T2, α 1<α2<α 3, L11>L21, L13<L23.The change of wherein main bearing structure and the shape of covering control
It is to be controlled by changing temperature in lip configuration closed cavity and pressure.
It is upper inclined state by intermediateness transition, due to T1 when inclined on inlet lip>T2, from booster pump to closing
High-temperature gas is filled in cavity, reaches memorial alloy transition temperature, main bearing structure is driven on lip configuration partially.Meanwhile antelabium
Structure drive device starts to drive antelabium to change its degree.According to calibration value, the first drive mechanism 5 drives flexible strand up and down respectively
Rope 7 so that antelabium degree reaches desired value α 1.
Table 1：Lip configuration discrete state and its control parameter
Step 2: according to the deformation of main bearing structure 1 and the corresponding relation of temperature and lip that are made up of memorial alloy
The temperature control rule of main bearing structure 1 described in shape design of control law, and antelabium knot is controlled according to lip shape design of control law
The first drive control rule of first drive mechanism of structure 3, and control the second drive control of the second servo-actuated drive mechanism of covering 2
Rule.
Step 3: obtaining current flight state, determine that lip shape control law corresponding to current flight state inputs, and according to
The input of secondary temperature control law, the input of the first drive control rule and the input of the second drive control rule；
Step 4: the input restrained according to temperature control controls the ratio of the cold air and hot gas in the closed cavity being made up of covering
Example output, meanwhile, the shape that input control antelabium is restrained according to antelabium drive control exports.
In the present embodiment, the step 3 also includes obtaining inlet lip shape under current flight state, and conduct
Data feedback is supplied to the first drive mechanism.
In the present embodiment, the step 3 also includes obtaining in the closed cavity being made up of covering under current flight state
Temperature and pressure, and give booster pump controlling organization as data feedback.
In the present embodiment, in the step 4, before cold air or hot gas are transported in the closed cavity, one is entered
Step includes the cold air being well mixed to certain temperature outside the closed cavity with the hot gas.
Specifically, marmem of the main bearing structure 1 using temperature controlled double-pass memory effect.Sealed by changing
Temperature in closed chamber body, realize the shape control to active deformation structure.Specific method is as follows：The surface edge of main bearing structure 1
Course and open up to temperature sensor 8, pressure transducer 11 and strain transducer 9 has been evenly arranged, closed cavity passes through air inlet
Cold air tank 13, hot gas tank 14 are connect respectively, are extended to multiple air inlets and exhaust outlet are evenly arranged, by air inlet, exhaust outlet
The monitoring of flow and pressure, it is ensured that when having high temperature or cryogenic gas enters the gas of fashionable intracavitary and can be sufficiently mixed, the temperature of intracavitary
It is uniform to spend field change, the pressure stability of intracavitary.When needing the temperature in adjusting cavity, the pressure in cavity need to be monitored, passes through flow
Control, makes the pressure in cavity not produce big fluctuation, the change of pressure is within ± 10%.When the temperature of intracavitary needs to improve
When, the air inlet of hot gas tank and the exhaust outlet of cavity are opened, the gas in hot gas tank enters cavity by booster pump supercharging
Interior, monitoring the numerical value of flow sensor 12 and pressure transducer 11 makes during air inlet, exhaust air pressure change in closed cavity
Steadily, and in real time the numerical value of temperature sensor 8 and strain transducer 9 is monitored, when the deformation of main bearing structure 1 reaches requirement,
Close air inlet, exhaust outlet.Similarly, when the temperature of intracavitary needs to reduce, the air inlet of cold air tank and the row of cavity are opened
Gas port, the gas in cold air tank are entered in cavity by booster pump supercharging, monitor flow sensor 12 and pressure transducer 11
Numerical value make during air inlet, exhaust that air pressure change is steady in closed cavity, and monitor temperature sensor 8 and strain in real time
The numerical value of sensor 9, when the deformation of main bearing structure 1 reaches requirement, closing air inlet, exhaust outlet.
Rigidity suitable material is chosen as covering 2, it is desirable to which the in-plane stiffness of covering 2 meets the deformation requirements of lip, covers
The shape of skin 2 is controlled by the distribution of lengths of the pressure in closed cavity and dimension shape cable wire 15.In order that covering 2 carries in outside
The shape needed is kept in the presence of lotus, is filled with gases at high pressure in closed cavity, the pressure of gases at high pressure need to reach aerodynamic loading
More than 15 times of pressure, and the air pressure change in holding chamber is in course of adjustment within ± 10%.
According to three discrete states of lip leading edge, the lip configuration drive device corresponding three in its portion within the cavity is determined
Individual stroke.Make deformation of the lip configuration 3 under different loads effect without departing from the control range of lip configuration drive device.Selection
Suitable lip material, it is desirable to the shape after the effect deformation of antelabium load, still can be in the driving scope of antelabium deformable structure
It is interior, calculate under lip configuration load effect outside, the external drive value needed under typical flying speed, and should to lip configuration
Change state is recorded, and as calibration value, controls lip configuration drive device, to reach the purpose for deforming lip configuration.
It is last it is to be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
The present invention is described in detail with reference to the foregoing embodiments for pipe, it will be understood by those within the art that：It is still
Technical scheme described in foregoing embodiments can be modified, or which part technical characteristic is equally replaced
Change；And these modifications or replacement, the essence of appropriate technical solution is departed from the essence of various embodiments of the present invention technical scheme
God and scope.
Claims (10)
1. a kind of inlet lip distressed structure, held comprising main bearing structure (1), covering (2) and lip configuration (3), the master
The one end for carrying structure (1) is fixed on cantilever support beam (4), and the other end connects the lip configuration (3), covering (2) bag
It is outside to overlay on the lip configuration (3), it is characterised in that：The inlet lip distressed structure also comprising temperature sensor (8),
Multiple strain transducer (9), temperature-adjusting device and lip configuration drive devices；
The main bearing structure (1) is manufactured using memory alloy material, and is arranged on the closed cavity of the covering (2) formation
It is interior；
The closed cavity is provided with air inlet and gas outlet；The temperature-adjusting device and the air inlet of the closed cavity connect
Connect, for adjusting the temperature in the closed cavity；
The temperature sensor (8) is arranged on the main bearing structure (1)；
The strain transducer (9) is arranged on the inner surface and the main bearing structure (1) of the covering (2)；
The lip configuration drive device is arranged on the main bearing structure (1), for driving the lip configuration (3).
2. inlet lip distressed structure as claimed in claim 1, it is characterised in that：The lip configuration (3), which includes, fixes
Portion (31) and adjustment portion (32), one end of the fixed part (31) is fixedly connected with one end of the adjustment portion (32), described solid
Determine portion (31) to be fixedly connected with the main bearing structure (1)；The one side of the adjustment portion (32) and the interior table of the covering (2)
Face is bonded, for supporting the covering (2), the opposite side relative with the inner surface of the covering (2) on the adjustment portion (32)
Strain transducer (9) is provided with face.
3. inlet lip distressed structure as claimed in claim 2, it is characterised in that：The lip configuration drive device includes
First drive mechanism (5), pulley (6) and flexible rope (7)；First drive mechanism (5) is fixed on the main bearing structure
(1) on, the pulley (6) is arranged between the lip configuration (3) and first drive mechanism (5)；The flexible rope
(7) pulley (6) is bypassed, one end is connected with first drive mechanism (5), and the other end is with the adjustment portion (32) away from solid
Determine one end connection in portion (31).
4. inlet lip distressed structure as claimed in claim 3, it is characterised in that：The inlet lip distressed structure is also
Comprising flow sensor (12) and pressure transducer (11), the flow sensor (12) and pressure transducer (11) are arranged on institute
State in main bearing structure (1)；The temperature-adjusting device includes cold air tank (13) and hot gas tank (14), the cold air tank (13) with
The air inlet connection of hot gas tank (14) the difference closed cavity.
5. inlet lip distressed structure as claimed in claim 4, it is characterised in that：The cold air tank (13) and hot gas tank
(14) booster pump is respectively arranged with, the booster pump is used to the gas in gas tank being sent into the closed cavity.
6. inlet lip distressed structure as claimed in claim 5, it is characterised in that：The inlet lip distressed structure is also
Comprising dimension shape cable wire (15), one end of the dimension shape cable wire (15) connects the inwall of the covering (2), and the other end connects the master
Bearing structure (1).
A kind of 7. inlet lip distressed structure control method, using the inlet lip as described in any one of claim 1 to 6
Distressed structure, it is characterised in that comprise the steps of：
Step 1: lip shape control law of the design aircraft under different flying speeds is required according to aircraft inlet engine compatibility, it is described
Inlet engine compatibility refers to the matching of air intake duct flow and engine；
Step 2: according to the deformation of main bearing structure and the corresponding relation of temperature and lip shape control that are made up of memorial alloy
System rule designs the temperature control rule of the main bearing structure, and controls the first of lip configuration according to lip shape design of control law
The first drive control rule of drive mechanism, and control the second drive control rule of the second servo-actuated drive mechanism of covering；
Step 3: obtaining current flight state, determine that lip shape control law corresponding to current flight state inputs, and it is true successively
The input of constant temperature degree control law, the input of the first drive control rule and the input of the second drive control rule；
Step 4: the cold air inputted in the closed cavity for controlling and being made up of covering and the ratio of hot gas restrained according to temperature control are defeated
Go out, meanwhile, the shape that input control antelabium is restrained according to antelabium drive control exports.
8. inlet lip distressed structure control method as claimed in claim 7, it is characterised in that：The step 3 also includes
Inlet lip shape under current flight state is obtained, and the first drive mechanism is supplied to as data feedback.
9. inlet lip distressed structure control method as claimed in claim 7, it is characterised in that：The step 3 also includes
The temperature and pressure in the closed cavity being made up of under current flight state covering are obtained, and booster pump control is given as data feedback
Mechanism processed.
10. inlet lip distressed structure control method as claimed in claim 7, it is characterised in that：In the step 4,
Before cold air or hot gas are transported in the closed cavity, further comprise the cold air and the hot gas in the closing
It is well mixed outside cavity to certain temperature.
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| CN201611050446.0A CN106703995B (en) | 2016-11-24 | 2016-11-24 | A kind of inlet lip distressed structure and inlet lip distressed structure control method |
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| CN107628228B (en) * | 2017-08-28 | 2020-09-18 | 中国航空工业集团公司沈阳飞机设计研究所 | Wing leading edge continuous bending structure |
| CN107628229B (en) * | 2017-08-28 | 2020-09-18 | 中国航空工业集团公司沈阳飞机设计研究所 | Truss type wing leading edge continuous variable camber structure |
| CN107829827A (en) * | 2017-11-29 | 2018-03-23 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of inlet lip structure |
| CN114753929B (en) * | 2022-02-28 | 2023-05-09 | 南京航空航天大学 | Memory alloy driven air inlet channel molded surface adjusting device, adjusting method and design method |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103047010A (en) * | 2012-11-28 | 2013-04-17 | 中国商用飞机有限责任公司 | Anti-icing system and anti-icing control method of inlet lip of engine |
| CN104314690A (en) * | 2014-10-21 | 2015-01-28 | 西北工业大学 | Plasma phase-changing control air inlet passage and control method |
| CN104481700A (en) * | 2014-09-25 | 2015-04-01 | 南京航空航天大学 | Combined dynamic axisymmetric variable geometry inlet, engine and air inlet control method |
| CN104931223A (en) * | 2015-06-03 | 2015-09-23 | 中国航天空气动力技术研究院 | Test apparatus capable of automatically adjusting scramjet inlet lip opening angle |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SG104914A1 (en) * | 1997-06-30 | 2004-07-30 | Hitachi Ltd | Gas turbine |
| US20120312023A1 (en) * | 2011-06-08 | 2012-12-13 | Honeywell International Inc. | Thermal management systems and methods for auxiliary power units |
-
2016
- 2016-11-24 CN CN201611050446.0A patent/CN106703995B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103047010A (en) * | 2012-11-28 | 2013-04-17 | 中国商用飞机有限责任公司 | Anti-icing system and anti-icing control method of inlet lip of engine |
| CN104481700A (en) * | 2014-09-25 | 2015-04-01 | 南京航空航天大学 | Combined dynamic axisymmetric variable geometry inlet, engine and air inlet control method |
| CN104314690A (en) * | 2014-10-21 | 2015-01-28 | 西北工业大学 | Plasma phase-changing control air inlet passage and control method |
| CN104931223A (en) * | 2015-06-03 | 2015-09-23 | 中国航天空气动力技术研究院 | Test apparatus capable of automatically adjusting scramjet inlet lip opening angle |
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