Simulation method and simulation device for aircraft battery

Abstract

The present invention discloses a simulation method and a simulation device for an aircraft battery, the simulation method for an aircraft battery comprising: determining the resistance of a thermistor at any operating temperature within a normal operating temperature range when the battery is in a normal power-on state; providing a first resistor with a fixed resistance value that is the same as the resistance value of the thermistor; determining the resistance of the internal load of the battery; providing a second resistor with a fixed resistance value that is the same as the resistance value of the internal load; providing a ground power supply and a connector; electrically connecting the first resistor between two interfaces of the connector, and connecting the second resistor in series between the ground power supply and the connector. The technical solution provided by the embodiment of the present invention can simulate the power supply signal of the battery to realize the function of simulating the battery, and realize power supply to the aircraft DC system when the aircraft battery is not installed, thereby avoiding the loss caused by repeated charging and discharging of the battery.

Description

Technical Field

[0001] The embodiments of the present invention relate to the technical field of electrical systems, and in particular to a simulation method and a simulation device for an aircraft battery. Background Art

[0002] The main uses of batteries on aircraft are: to serve as auxiliary power or emergency power to supply power to important electrical equipment when the aircraft's main power supply is not working or fails; to serve as a starting power source for aircraft engines; and in some special cases (such as in the wild without power supply) to power some aircraft's low-power electrical equipment for pre-flight inspection. When aircraft batteries are used as emergency power sources, they are often used in parallel with a DC generator (main power source).

[0003] At present, when the DC power supply is powered on, the connector on the aircraft needs to be connected to the interface on the battery. The battery outputs temperature and voltage signals to the data concentrator and the battery control device. Based on the received signals, the battery control device determines what working state the battery should be in, such as: charging, discharging or isolation. The data concentrator sends a signal to the display to display the parameter value on the schematic page. However, there is currently no method to simulate the battery, which means that after the battery is installed, it may be repeatedly charged and discharged, resulting in a large loss of the battery. Summary of the invention

[0004] The embodiment of the present invention provides a simulation method and a simulation device for an aircraft battery, so as to realize the function of simulating a battery, and to supply power to an aircraft DC system when the aircraft battery is not installed, thereby avoiding the loss caused by repeated charging and discharging of the battery.

[0005] An embodiment of the present invention provides a simulation method for an aircraft battery, and the simulation method for an aircraft battery includes:

[0006] Determine the resistance value of the thermistor at any operating temperature within the normal operating temperature range when the battery is normally powered on;

[0007] Providing a first resistor having a fixed resistance value which is the same as the resistance value of the thermistor;

[0008] Determine the resistance of the battery's internal load;

[0009] providing a second resistor having a fixed resistance value which is the same as the resistance value of the resistor of the internal load;

[0010] Provide ground power supply and connector;

[0011] The first resistor is electrically connected between two interfaces of the connector, and the second resistor is connected in series between the ground power supply and the connector.

[0012] In one embodiment, determining the resistance value of the thermistor at any operating temperature within the normal operating temperature range when the battery is in a normal power-on state includes:

[0013] providing a battery;

[0014] Power on the battery normally, and record the temperature T of the battery when it is working normally;

[0015] Placing the battery in an environment at temperature T for at least one hour;

[0016] Detect the resistance value of the thermistor of the battery.

[0017] In one embodiment, determining the resistance of the internal load of the battery includes:

[0018] A test resistor with a resistance value of R0 is electrically connected in series between the positive electrode and the negative electrode of the battery;

[0019] Test the voltage across the test resistor, denoted as UR0;

[0020] Calculating the resistance of the internal load of the battery;

[0021] The calculation formula is: R1 = R2 = [UP / (UR0 / R0)-R0] / 2;

[0022] Wherein, UP is the voltage between the positive and negative electrodes of the battery, and R1 and R2 are the resistances of the internal loads at the positive and negative terminals, respectively.

[0023] In one embodiment, the connector includes a first connector and a second connector;

[0024] The positive electrode interface and the negative electrode interface of the first connector are electrically connected to the positive electrode and the negative electrode of the ground power supply respectively;

[0025] The positive electrode interface of the second connector is electrically connected to the positive electrode of the ground power supply through a second A resistor, and the negative electrode interface of the second connector is electrically connected to the negative electrode of the ground power supply through a second B resistor; the resistance values ​​of the second A resistor and the second B resistor are equal to the resistance values ​​of the internal loads of the positive terminal and the negative terminal, respectively.

[0026] In one embodiment, the second connector includes a plurality of groups of interfaces connected to the first resistor;

[0027] The resistance of each first resistor is respectively equal to the resistance of the thermistor of different batteries.

[0028] In one embodiment, providing a ground power supply and a connector includes:

[0029] Provide ground power to meet aircraft DC system requirements;

[0030] Provide a connector of the same type as the battery described.

[0031] An embodiment of the present invention further provides an aircraft battery simulation device, which is formed by any of the above aircraft battery simulation methods, and includes: a ground power supply, a connector, a first resistor and a second resistor;

[0032] The first resistor is electrically connected between two interfaces of the connector, and the second resistor is connected in series between the ground power supply and the connector.

[0033] In one embodiment, the connector includes a first connector and a second connector;

[0034] The positive electrode interface and the negative electrode interface of the first connector are electrically connected to the positive electrode and the negative electrode of the ground power supply respectively;

[0035] The positive electrode interface of the second connector is electrically connected to the positive electrode of the ground power supply through a second A resistor, and the negative electrode interface of the second connector is electrically connected to the negative electrode of the ground power supply through a second B resistor; the resistance values ​​of the second A resistor and the second B resistor are respectively equal to the resistance values ​​of the internal loads of the positive and negative terminals of the battery.

[0036] The simulation method of an aircraft battery provided by an embodiment of the present invention includes: determining the resistance value of a thermistor at any operating temperature within a normal operating temperature range when the battery is in a normal power-on state; providing a first resistor with a fixed resistance value that is the same as the resistance value of the thermistor; determining the resistance of the internal load of the battery; providing a second resistor with a fixed resistance value that is the same as the resistance value of the internal load; providing a ground power supply and a connector; electrically connecting the first resistor between two interfaces of the connector, and connecting the second resistor in series between the ground power supply and the connector. Thus, through the coordinated electrical connection between the ground power supply, the connector, the first resistor, and the second resistor, the power supply signal of the battery can be simulated to realize the function of simulating the battery, and when the aircraft battery is not installed, power is supplied to the aircraft DC system to avoid the loss caused by repeated charging and discharging of the battery. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0038] Figure 1is a structural schematic diagram of an aircraft battery provided by an embodiment of the present invention;

[0039] Figure 2 is a flow chart of a simulation method for an aircraft battery provided by an embodiment of the present invention;

[0040] Figure 3 yes Figure 2 A schematic diagram of a simulation signal interface in the simulation method shown;

[0041] Figure 4 The present invention is a schematic structural diagram of a simulation device for an aircraft battery provided in an embodiment of the present invention. DETAILED DESCRIPTION

[0042] The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are only used to explain the present invention, rather than to limit the present invention. It should also be noted that, for ease of description, only parts related to the present invention, rather than all structures, are shown in the accompanying drawings.

[0043] The improvements of the simulation method and simulation device of the aircraft battery (hereinafter also referred to as "battery") provided by the embodiment of the present invention at least include: providing a method for simulating battery power supply, using a ground power supply, a connector, a first resistor and a second resistor to coordinate electrical connection, and simulating the output signal of the battery to realize the DC power supply function of the simulated battery, so that when the aircraft battery is not installed, it is possible to power the aircraft DC system, thereby avoiding the loss caused by repeated charging and discharging of the battery.

[0044] Combine the following Figure 1-Figure 4 , the simulation method and simulation device of the aircraft battery provided by the embodiment of the present invention are exemplarily described.

[0045] Reference Figure 1 The aircraft battery 01 includes a battery body and a first output port 011 and a second output port 012: wherein the first output port 011 is used to supply power to the aircraft DC system, and the second output port 012 is used to output a temperature signal and a voltage signal, so as to realize power supply to the aircraft after the battery is installed, and at the same time realize the monitoring of the power supply status.

[0046] Among them, in the related technology, after the battery is installed, some system equipment is powered by the battery, and the battery is in a discharging state at this time; when the aircraft detects that the battery power is insufficient, the battery enters a charging state. Therefore, once the battery is installed, it will enter a cyclic charging and discharging state, and the battery loss is relatively serious.

[0047] The embodiment of the present invention simulates the function of the battery according to the normal power supply state of the battery by using the ground power supply, the connector, the first resistor and the second resistor, and can supply power to the aircraft DC system when the battery is not installed, thereby avoiding the loss caused by repeated charging and discharging of the battery.

[0048] For example, refer to Figure 2 , the aircraft battery simulation method may include:

[0049] S110, determining the resistance value of the thermistor at any operating temperature within the normal operating temperature range when the battery is in a normal powered-on state.

[0050] Among them, the battery can work normally within a normal working temperature range limited by an upper temperature limit and a lower temperature limit. The simulation method provided by the embodiment of the present invention can select any working temperature within the above normal working temperature range as the simulated working temperature; the resistance value of the thermistor at the working temperature is a reference basis for the resistance value of the first resistor in the battery simulation method.

[0051] Exemplarily, when the normal operating temperature range is 20°C-60°C, the optional temperature values ​​include 20°C, 60°C, 40°C or other temperature values ​​within the above temperature range, which will not be elaborated in the embodiments of the present invention.

[0052] In other implementations, the normal operating temperature range may vary with different battery models, which is not limited in the embodiments of the present invention.

[0053] Based on this, this step may include testing, reading or calculating the resistance value of the thermistor of the battery at a normal operating temperature to prepare for S120.

[0054] S120 , providing a first resistor having a fixed resistance value that is the same as that of the thermistor.

[0055] Based on S110, this step may include: selecting a resistor with the same resistance value as that determined in S110 as the first resistor.

[0056] Thus, S110 and S120 complete the simulation of the temperature sensor in the battery.

[0057] S130. Determine the resistance of the internal load of the battery.

[0058] This step prepares for the analog voltage sensor.

[0059] S140 , providing a second resistor with a fixed resistance value that is the same as the resistance value of the internal load.

[0060] Based on S130, the next step may include: selecting a resistor having the same resistance value as that determined in S130 as the second resistor.

[0061] Thus, S130 and S140 complete the simulation of the voltage sensor in the battery.

[0062] S150, provide ground power supply and connector.

[0063] This step is to prepare for simulating the connection and power supply of the battery.

[0064] S160, electrically connect a first resistor between two interfaces of the connector, and connect a second resistor in series between the ground power supply and the connector.

[0065] On the basis of S110 - S150 , this step electrically connects the ground power supply, the connector, the first resistor and the second resistor in a coordinated manner to simulate battery power supply.

[0066] In other implementations, the voltage sensor simulation may be performed first and then the temperature sensor simulation, that is, S130 and S140 are performed before S110 and S120, which is not limited in the embodiment of the present invention.

[0067] Next, Figure 2 The steps shown in the figure are described in detail by way of example.

[0068] In one embodiment, S110 may include:

[0069] Step 1: Provide a battery.

[0070] Among them, the temperature sensor in the battery can be a thermistor, and the battery model is adapted to the aircraft model.

[0071] Step 2: Power on the battery normally and record the temperature T of the battery when it is working normally.

[0072] Exemplarily, the temperature T of the battery when it is operating normally is recorded according to the parameters displayed on the power schematic page in the normal power-on state.

[0073] Step 3: Place the battery in an environment with temperature T for at least one hour.

[0074] This step can stabilize the temperature of the battery, so that a stable and relatively accurate resistance value can be measured in the next step.

[0075] Exemplarily, the placement time may be one hour, or a time period greater than one hour, and may be set according to requirements of the simulation method, which is not limited in the embodiment of the present invention.

[0076] Step 4: Detect the resistance of the battery thermistor.

[0077] Exemplarily, it may include detecting the resistance value between pinholes of the temperature sensor circuit of the battery to obtain the resistance value of the thermistor at normal temperature.

[0078] So far, a simulation basis for the temperature sensor in the battery has been formed.

[0079] In one embodiment, S130 may include:

[0080] Step 1: Connect a test resistor with a resistance value of R0 in series between the positive and negative electrodes of the battery.

[0081] The voltage sensor in the battery can directly detect the voltage between the positive and negative electrodes of the battery, and two loads are connected in series in the circuit, whose resistance values ​​are represented by R1 and R2 respectively. To calculate the resistance value of the load, a resistor R0 with a fixed resistance value (for example, 10K ohms) can be connected in series outside the battery.

[0082] Step 2: Test the voltage across the test resistor, recorded as UR0.

[0083] This step prepares for the subsequent calculation of the resistance value of the internal load.

[0084] Exemplarily, this step may include: using a multimeter to measure the voltage value across the test resistor, which is UR0.

[0085] Step 3: Calculate the resistance of the internal load of the battery.

[0086] The calculation formula is: R1=R2=[UP / (UR0 / R0)-R0] / 2; wherein UP is the voltage between the positive and negative electrodes of the battery, and R1 and R2 are the resistances of the internal loads at the positive and negative electrodes, respectively.

[0087] UP can also be understood as the voltage value of the battery when it is working normally (for example, the voltage value of the aircraft battery when it is working normally may be 28V).

[0088] For example, the analog signal interface diagram of the battery can be as follows: Figure 3 See Figure 3 , where interface 6 and interface 13 are positive and negative interfaces, which can be electrically connected to the positive and negative electrodes of the ground power supply through the load at the positive end (shown by R1) and the load at the negative end (shown by R2) respectively; interface 7 and interface 8, interface 9 and interface 10, interface 11 and interface 12 are three groups of signal interfaces, which can provide the temperature information of the battery to three different devices of the aircraft, and the resistance value of the resistor represents the temperature (shown by T1, T2 and T3 in the figure). This figure can be understood as a circuit simulation diagram inside the battery. In the real internal circuit of the battery, the temperature is sensed by thermistor.

[0089] In one embodiment, S150 may include:

[0090] Step 1: Provide ground power that meets the aircraft DC system requirements.

[0091] In this step, it is necessary to select a suitable ground power supply adapted to the aircraft DC system to avoid excessive processing of the ground power supply, thereby facilitating the simplification of the simulation method.

[0092] Step 2: Provide a connector of the same model as the battery.

[0093] Among them, the connectors of different models and different types of batteries may be different, so it is necessary to select a connector that is the same as the battery model to achieve battery simulation.

[0094] In one embodiment, reference may be made to Figure 4 The connector 220 includes a first connector 221 (also shown as "J1" in the figure) and a second connector 222 (also shown as "J2" in the figure); the positive electrode interface (shown as "﹢") and the negative electrode interface (shown as "-") of the first connector 221 are electrically connected to the positive electrode (shown as "﹢") and the negative electrode (shown as "-") of the ground power supply respectively; the positive electrode interface of the second connector 222 is electrically connected to the positive electrode of the ground power supply 210 through the second A resistor (shown as R1), and the negative electrode interface of the second connector 222 is electrically connected to the negative electrode of the ground power supply 210 through the second B resistor (shown as R2); the resistance values ​​of the second A resistor and the second B resistor are equal to the resistance values ​​of the resistances of the internal loads at the positive end and the negative end, respectively.

[0095] The selection of the connector varies according to the type of the battery, that is, the connector is adapted to the simulated battery. Figure 4 In the description, only the example of the connector including the first connector and the second connector is used. In other embodiments, the structural form of the connector 220 can also be other forms selected according to the battery, and the embodiment of the present invention is not limited to this.

[0096] So far, Figure 4 The circuit structure shown in can simulate the power supply function of the battery.

[0097] In one embodiment, continue to refer to Figure 4 The second connector 220 includes a plurality of groups of first resistors (respectively R T1 , R T2 and R TN The interface (shown) Figure 4In the second connector 220 shown, interfaces 2 and 3, interfaces 4 and 5, interfaces 6 and 7 are respectively grouped together to connect a resistor for simulating a temperature sensor); wherein the resistance of each first resistor is respectively equal to the resistance of thermistors of different batteries.

[0098] For example, different models of aircraft, even if the same nickel-cadmium battery (a storage battery) is used, may have 3, 4 or more groups of output temperature signals. In order to illustrate that the simulation method of the aircraft battery is applicable to different models, N groups of signals are used as identifiers (R T1 , R T2 and R TN , one resistor represents a set of temperature signals).

[0099] It should be noted that what is used here is not a thermistor, but a first resistor with a fixed resistance value selected based on the resistance value measured at the normal temperature T in the above text, so as to ensure that the temperature signal obtained by the aircraft is always in a normal state.

[0100] On the basis of the above embodiments, the embodiments of the present invention further provide a simulation device for an aircraft battery, which can be formed by the simulation method for an aircraft battery provided by any of the above embodiments. Therefore, the simulation device for an aircraft battery also has the technical effects of the simulation method for an aircraft battery, which can be understood by referring to the above text and will not be described in detail here.

[0101] For example, see Figure 4 The aircraft battery simulation device 20 includes: a ground power supply 210, a connector 220, a first resistor (respectively R T1 , R T2 and R TN ) and a second resistor (shown as R1 and R2 respectively); wherein the first resistor is electrically connected between the two interfaces of the connector 220 to simulate the temperature sensor of the battery; and the second resistor is connected in series between the ground power supply 210 and the connector 220 to simulate the voltage sensor of the battery.

[0102] In one embodiment, the connector 220 includes a first connector 221 (or represented by "J1") and a second connector 222 (or represented by "J2"); the positive electrode interface and the negative electrode interface of the first connector 221 are electrically connected to the positive electrode and the negative electrode of the ground power supply, respectively; the positive electrode interface of the second connector 222 is electrically connected to the positive electrode of the ground power supply 210 through a second A resistor (shown as R1), and the negative electrode interface of the second connector 222 is electrically connected to the negative electrode of the ground power supply 210 through a second B resistor (shown as R2); the resistance values ​​of the second A resistor and the second B resistor are equal to the resistance values ​​of the internal loads of the positive terminal and the negative terminal, respectively.

[0103] The selection of the connector varies according to the type of the battery, that is, the connector is adapted to the simulated battery. Figure 4 In the description, only the example in which the connector includes a first connector and a second connector is used.

[0104] So far, Figure 4 The circuit structure shown in can simulate the power supply function of the battery.

[0105] In other implementations, the structural form of the connector 220 may also be other forms selected according to the battery, and may be set according to the requirements of the battery simulation device 20, which is not limited in the embodiment of the present invention.

[0106] Note that the above are only preferred embodiments of the present invention and the technical principles used. Those skilled in the art will understand that the present invention is not limited to the specific embodiments described herein, and that various obvious changes, readjustments and substitutions can be made by those skilled in the art without departing from the scope of protection of the present invention. Therefore, although the present invention has been described in more detail through the above embodiments, the present invention is not limited to the above embodiments, and may include more other equivalent embodiments without departing from the concept of the present invention, and the scope of the present invention is determined by the scope of the appended claims.

Claims

1. A method for simulating an aircraft battery, characterized in that: include: Determine the resistance value of the thermistor at any operating temperature within the normal operating temperature range when the battery is normally powered on; Providing a first resistor having a fixed resistance value which is the same as the resistance value of the thermistor; Determine the resistance of the battery's internal load; providing a second resistor having a fixed resistance value which is the same as the resistance value of the resistor of the internal load; Provide ground power supply and connector; The first resistor is electrically connected between the two interfaces of the connector, and the second resistor is connected in series between the ground power supply and the connector; The two interfaces are a set of signal interfaces for providing the temperature information of the battery to the equipment of the aircraft.

2. The method for simulating an aircraft battery according to claim 1, characterized in that: Determine the resistance of the thermistor at any operating temperature within the normal operating temperature range when the battery is normally powered on: providing a battery; Power on the battery normally, and record the temperature T of the battery when it is working normally; Placing the battery in an environment at temperature T for at least one hour; Detect the resistance value of the thermistor of the battery.

3. The aircraft battery simulation method according to claim 1, characterized in that: Determine the resistance of the battery's internal load including: A test resistor with a resistance value of R0 is electrically connected in series between the positive electrode and the negative electrode of the battery; Test the voltage across the test resistor, denoted as UR0; Calculating the resistance of the internal load of the battery; The calculation formula is: R1 = R2 = [UP / (UR0 / R0)-R0] / 2; Wherein, UP is the voltage between the positive and negative electrodes of the battery, and R1 and R2 are the resistances of the internal loads at the positive and negative terminals, respectively.

4. The aircraft battery simulation method according to claim 3, characterized in that: The connector includes a first connector and a second connector; the second resistor includes a second A resistor and a second B resistor; The positive electrode interface and the negative electrode interface of the first connector are electrically connected to the positive electrode and the negative electrode of the ground power supply respectively; The positive electrode interface of the second connector is electrically connected to the positive electrode of the ground power supply through a second A resistor, and the negative electrode interface of the second connector is electrically connected to the negative electrode of the ground power supply through a second B resistor; the resistance values ​​of the second A resistor and the second B resistor are equal to the resistance values ​​of the internal loads of the positive terminal and the negative terminal, respectively.

5. The aircraft battery simulation method according to claim 4, characterized in that: The second connector includes a plurality of interfaces connected to the first resistor; The resistance of each first resistor is respectively equal to the resistance of the thermistor of different batteries.

6. The aircraft battery simulation method according to claim 1, characterized in that: Provides ground power and connectors including: Provide ground power to meet aircraft DC system requirements; Provide a connector of the same type as the battery described.

7. A simulation device for an aircraft battery, characterized in that: The aircraft battery simulation method according to any one of claims 1 to 6 is used to form the battery, comprising: a ground power supply, a connector, a first resistor and a second resistor; The first resistor is electrically connected between two interfaces of the connector, and the second resistor is connected in series between the ground power supply and the connector.

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