CN101590914A - A kind of anti-icing and deicing device for flight vehicle - Google Patents

Abstract

The invention discloses a kind of anti-icing and deicing device for flight vehicle, comprise icing detecting unit, data processing unit, interface circuit and electric heating unit; Described icing detecting unit is used for detecting ice layer thickness information, and export to data processing unit with the form of voltage or electric current or frequency, after handling this voltage or electric current or frequency signal, data processing unit obtains the profile of layers of ice, export the deicing control signal simultaneously, this deicing control signal converts working current to by interface circuit then, and working current enters electric heating unit and carries out deicing.Device accuracy of detection height of the present invention, antijamming capability is strong, and speed of response is fast; Apparatus structure is simple, is convenient to Project Realization.The present invention is applicable to that aircraft, guided missile etc. have the field of high speed, high efficiency requirement to anti-icing, deicing.

Description

A kind of anti-icing and deicing device for flight vehicle

Technical field

The present invention relates to a kind of intelligent anti-icing and de-icing device of aircraft, belong to the safety protection technique field, particularly rapidly and efficiently anti-icing application engineering is applicable to that aircraft, guided missile etc. have the field of high speed, high efficiency requirement to anti-icing, deicing.

Background technology

The safety of ice formation issues serious harm aircraft, guided missile.Ice sheet appears in aircraft surface, can seriously hinder flowing of air, increases aerodynamic drag; Especially the ice pole the earth on the aerofoil changes its aerodynamic configuration, and lift is sharply reduced; The ice cube of front of the engine very easily is inhaled into the driving engine of high speed rotating when coming off, cause power failure.When aircraft passed through the cloud layer that contains super-cooling waterdrop, it was common phenomena very that its surface freezes, and especially when the aircraft high-speed flight, icing rate is exceedingly fast, and can reach 60～100 mm/second.How the technical bottleneck of current solution aircraft ice formation issues is to reduce the risk that aircraft surface freezes as far as possible soon and effectively under the prerequisite that influences the aircraft aerodynamic configuration as small as possible.

For preventing that aircraft surface from freezing, existing icing predicting means mainly contains two kinds: artificial visually examine and fixed position are detected; Anti-icing technology mainly contains two kinds: continue the heating of heating and manual control.The artificial visually examine can not judge icing situation timely and accurately; The position that lays of conventional freezing sensor is influenced by aerodynamic configuration, and can have a negative impact to aerodynamic arrangement inevitably.The deicing means that continue heating are not handled the icing situation of aircraft surface with making any distinction between, can cause deicing deficiency and superheated, and not only the heat service efficiency is low, and can cause aircraft accident under the situation of deicing deficiency; The drawback of lasting heating has been avoided in the manual control heating, but has the situation that artificial judgment is untimely and judge by accident simultaneously.

Therefore above-mentioned detection and de-icing method all are not suitable for aircraft and guided missile etc. and require the anti-icing safety protection field of high-speed and high-efficiency.

Summary of the invention

The objective of the invention is provides a kind of anti-icing and de-icing device that satisfies the anti-icing needs of high-speed and high-efficiency in order to overcome existing various detections and deficiency anti-icing, de-icing method.

A kind of anti-icing and deicing device for flight vehicle comprises icing detecting unit, data processing unit, interface circuit and electric heating unit;

Described icing detecting unit is used for detecting ice layer thickness information, and export to data processing unit with the form of voltage or electric current or frequency, after handling this voltage or electric current or frequency signal, data processing unit obtains the profile of layers of ice, export a deicing control signal simultaneously, this deicing control signal converts working current to by interface circuit then, and working current enters electric heating unit and begins to heat ice sheet.

The invention has the advantages that:

(1) sensor bulk of icing detecting unit employing of the present invention is little, in light weight, can ignore the aerodynamic configuration influence of aircraft;

(2) the resonant mode freezing sensor is output as frequency output, and antijamming capability is strong; Apparatus of the present invention are simple in structure, are easy to batch manufacturing;

(3) electric heating unit adopts the heavy current pulse heating, and speed of response is fast, electric heating utilization ratio height.

Description of drawings

Structural representation when Fig. 1 adopts the resonant mode freezing sensor for the present invention;

Fig. 2 is the resonance beam scheme drawing under the surperficial no ice condition condition of the resonance beam of freezing sensor;

Fig. 3 is that the resonance beam surface of freezing sensor has the resonance beam scheme drawing under the ice condition condition;

Fig. 4 forms flute profile embacle scheme drawing for the leading edge of a wing;

Fig. 5 is the wing flute profile embacle scheme drawing that breaks;

Fig. 6 is strong instantaneous current of triangular pulse electric current and little average current scheme drawing.

Among the figure:

The 1-detecting unit 2-data processing unit 3-interface circuit 4-electric heating unit that freezes

101-resonant mode freezing sensor 401-heater strip 5-resonance beam

The specific embodiment

The present invention is described in further detail below in conjunction with drawings and Examples.

The present invention is a kind of anti-icing and deicing device for flight vehicle, as shown in Figure 1, comprises freeze detecting unit 1, data processing unit 2, interface circuit 3 and electric heating unit 4; Described icing detecting unit 1 is used for detecting ice layer thickness information, and export to data processing unit 2 with the form of voltage or electric current or frequency, after handling, 2 pairs of these voltages of data processing unit or electric current or frequency signal obtain the profile of layers of ice, export a deicing control signal simultaneously, this deicing control signal converts working current to by interface circuit 3 then, and working current enters electric heating unit 4 and begins to heat ice sheet.

The detecting unit 1 that freezes comprises several freezing sensors, and described freezing sensor is resonant mode freezing sensor 101 or condenser freezing sensor or reflective freezing sensor of light or conductance type freezing sensor.Data processing unit 2 adopts dsp processor or FPGA treater or micro controller system or arm processor; Described electric heating unit 4 comprises several heating wire or Electric radiant Heating Film or electro heat fiber; Described interface circuit 3 can adopt thyristor.

When icing detecting unit 1 comprises n resonant mode freezing sensor 101, when electric heating unit 4 comprised m heating wire, as shown in Figure 1, resonant mode freezing sensor 101 is distributed in aircraft needed position anti-icing, deicing; Difference according to resonant mode freezing sensor 101 distributing positions is divided into the k group with resonant mode freezing sensor 101, and data processing unit 2 is connected with resonant mode freezing sensor 101, the resonant frequency f of resonant mode freezing sensor 101 outputs _Xi(i=1,2 ..., n), send data processing unit 2 to.Data processing unit 2 is with the resonant frequency f of i resonant mode freezing sensor 101 outputs _XiWith its natural frequency f _0iAsk poor, obtain resonance frequency shift amount Δ f _i, described resonance frequency shift amount Δ f _iWith ice layer thickness be monotonically increasing;

As shown in Figure 2, when on the resonance beam 5 ice sheet being arranged, the resonant frequency f of described resonant mode freezing sensor 101 outputs _XiFor:

$f_{\mathrm{xi}}=\frac{1}{2\mathrm{\π}}\sqrt{\frac{k_{\mathrm{xi}}}{m_{\mathrm{xi}}}}---\left(1\right)$

Wherein, i is the numbering of resonant mode freezing sensor 101, i=1, and 2 ..., n, k _XiBe the equivalent stiffness of resonance beam after i resonant mode freezing sensor 101 freezes, m _XiIt is the equivalent mass of resonance beam after i resonant mode freezing sensor 101 freezes;

As shown in Figure 3, when not having ice on the resonance beam 5, the natural frequency f of described resonant mode freezing sensor 101 under no ice state _0iFor:

$f_{0i}=\frac{1}{2\mathrm{\π}}\sqrt{\frac{k_{0i}}{m_{0i}}}---\left(2\right)$

Wherein, k _0iBe the equivalent stiffness that i resonant mode freezing sensor 101 do not have resonance beam when icing, m _0iIt is the equivalent mass that i resonant mode freezing sensor 101 do not have resonance beam when icing;

The resonance frequency shift amount Δ f of described resonant mode freezing sensor 101 _iBy:

$\mathrm{\Δ}{f}_i=\frac{1}{2\mathrm{\π}}\sqrt{\frac{k_{\mathrm{xi}}}{m_{\mathrm{xi}}}}-\frac{1}{2\mathrm{\π}}\sqrt{\frac{k_{0i}}{m_{0i}}}---\left(3\right)$

Obtain.

Data processing unit 2 is with the k group resonance frequency shift amount Δ f that obtains _iAdopt the conic fitting algorithm to obtain the profile of layers of ice respectively, distribute and resemblance selection heating strategy by ice layer thickness.Described heating strategy is meant at the ice sheet thin location and adds heat-flash, reduces heating power at the ice sheet thicker part; Send the deicing control signal for interface circuit 3 according to the heating strategy of choosing; Interface circuit 3 is realized the conversion of control signal to working current, and low level deicing control signal is converted into pulse high current I _j, j=1,2 ..., m.Pulse high current I _jBe controlled instantaneous superpower and less average power, pulse high current I _jEnter electric heating unit 4, m pulse high current I _jEnter m electric heating 401 of electric heating unit, produce the deicing heat distribution of expectation.Described pulse high current, its waveform comprises sawtooth wave, chopping sea and square wave.

When icing detecting unit 1 comprises n condenser freezing sensor, the output capacitance C of described condenser freezing sensor _XiFor:

C _xi＝k·ε _xiS (4)

Wherein, i is the numbering of condenser freezing sensor, and k is a proportionality coefficient, ε _XiBe that relative dielectric constant between capacitor plate is detected in i the condenser freezing sensor back that freezes, S be i condenser freezing sensor detection capacitor plate over against area;

The output capacitance C of described condenser freezing sensor under no ice state _0iFor:

C _0i＝k·ε _0iS (5)

Wherein, ε _0iBe that i condenser freezing sensor do not have the relative dielectric constant that detects when icing between capacitor plate;

The electric capacity offset C of described condenser freezing sensor _iBy:

ΔC _i＝k·ε _xiS-k·ε _0iS (6)

Obtain.

Data processing unit 2 is with the k group electric capacity offset C that obtains _iAdopt the conic fitting algorithm to obtain the profile of layers of ice respectively, distribute and resemblance selection heating strategy by ice layer thickness.It is described when interface circuit 3 and electric heating unit 4 workflows adopt resonant mode freezing sensor 101 with the detecting unit 1 that freezes.

A kind of anti-icing and deicing device for flight vehicle of the present invention, weakness at ice sheet adds instantaneous strong current pulse, make ice sheet fracture occur, make simultaneously and form moisture film between ice sheet and the aircraft top layer, the incoming flow that produces in aircraft flight brushes under the effect, ice sheet can come off rapidly, thereby reaches purpose anti-, deicing.As shown in Figure 4, leading edge at wing has the flute profile embacle, leading edge surface at wing, the below that is the flute profile embacle distributes with 3 heater strips 401, the flute profile embacle influences the place ahead incoming flow of wing, destroy the aerodynamic configuration of wing, as shown in Figure 5, the heating wire 401 instantaneous strong current pulse that add at flute profile embacle ice groove place, instantaneous strong current pulse as shown in Figure 6, abscissa is the time, ordinate is an electric current, instantaneous strong current pulse is a chopping sea, and current peak is higher more than 10 times than average current, and instantaneous high heat makes the flute profile embacle from the fracture of ice groove, form moisture film between ice sheet and the wing top layer simultaneously, under the incoming flow effect, the flute profile embacle comes off rapidly both sides up and down to wing, as Fig. 5 forwardly.

Claims (7)

1, a kind of anti-icing and deicing device for flight vehicle is characterized in that: comprise icing detecting unit, data processing unit, interface circuit and electric heating unit;

Described icing detecting unit is used for detecting ice layer thickness information, and export to data processing unit with the form of voltage or electric current or frequency, after handling this voltage or electric current or frequency signal, data processing unit obtains the profile of layers of ice, export the deicing control signal simultaneously, this deicing control signal converts working current to by interface circuit then, and working current enters electric heating unit and carries out deicing;

Described icing detecting unit comprises several resonant mode freezing sensors or condenser freezing sensor or reflective freezing sensor of light or conductance type freezing sensor;

Described data processing unit adopts dsp processor or FPGA treater or micro controller system or arm processor;

Described electric heating unit comprises several heating wire, Electric radiant Heating Film or electro heat fiber.

2, a kind of anti-icing and deicing device for flight vehicle according to claim 1 is characterized in that: the resonant mode freezing sensor is distributed in that the aircraft needs are anti-icing, the position of deicing; Difference according to resonant mode freezing sensor distributing position is divided into the k group with the resonant mode freezing sensor, and data processing unit is connected with the resonant mode freezing sensor, the resonant frequency f of resonant mode freezing sensor output _XiSend data processing unit to.

3, a kind of anti-icing and deicing device for flight vehicle according to claim 1 is characterized in that: data processing unit is with the resonant frequency f of i resonant mode freezing sensor output _XiWith its natural frequency f _0iAsk poor, obtain resonance frequency shift amount Δ f _i, described resonance frequency shift amount Δ f _iWith ice layer thickness be monotonically increasing, then with the k that obtains group resonance frequency shift amount Δ f _iAdopt the conic fitting algorithm to obtain the profile of layers of ice respectively, distribute and resemblance selection heating strategy by ice layer thickness.

4, according to claim 2 or 3 described a kind of anti-icing and deicing device for flight vehicle, it is characterized in that: the resonant frequency f of described resonant mode freezing sensor output _XiFor:

$f_{\mathrm{xi}}=\frac{1}{2\mathrm{\π}}\sqrt{\frac{k_{\mathrm{xi}}}{m_{\mathrm{xi}}}}---\left(1\right)$

Wherein, i is the numbering of resonant mode freezing sensor, i=1, and 2 ..., n, k _XiBe the equivalent stiffness of resonance beam after i resonant mode freezing sensor freezes, m _XiIt is the equivalent mass of resonance beam after i resonant mode freezing sensor freezes;

The natural frequency f of described resonant mode freezing sensor _0iFor:

$f_{0i}=\frac{1}{2\mathrm{\π}}\sqrt{\frac{k_{0i}}{m_{0i}}}---\left(2\right)$

Wherein, k _0iBe the equivalent stiffness that i resonant mode freezing sensor do not have resonance beam when icing, m _0iIt is the equivalent mass that i resonant mode freezing sensor do not have resonance beam when icing;

The resonance frequency shift amount Δ f of described resonant mode freezing sensor _iBy:

${\mathrm{\Δf}}_i=\frac{1}{2\mathrm{\π}}\sqrt{\frac{k_{\mathrm{xi}}}{m_{\mathrm{xi}}}}-\frac{1}{2\mathrm{\π}}\sqrt{\frac{k_{0i}}{m_{0i}}}---\left(3\right)$

Obtain.

5, a kind of anti-icing and deicing device for flight vehicle according to claim 3 is characterized in that: described heating strategy is meant at the ice sheet thin location and adds heat-flash, reduces heating power at the ice sheet thicker part; Send the deicing control signal according to the heating strategy of choosing to interface circuit; Interface circuit is realized the conversion of control signal to working current, and low level deicing control signal is converted into pulse high current I _j, pulse high current I _jEnter electric heating unit, produce the deicing heat distribution of expectation.

6, a kind of anti-icing and deicing device for flight vehicle according to claim 5 is characterized in that: described pulse high current, its waveform comprises sawtooth wave, chopping sea and square wave.

7, a kind of anti-icing and deicing device for flight vehicle according to claim 1 is characterized in that: described interface circuit adopts thyristor.

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