Airplane cargo hold area heating function starting temperature condition simulation system

Abstract

The utility model discloses an airplane cargo hold area heating function starting temperature condition simulation system. The system comprises a resistance adjustment test tool device, an aircraft cargo hold area temperature sensor and an air conditioner management controller. The resistance adjustment test tool equipment is electrically connected in parallel with the temperature sensor at the airplane cargo hold area; and the temperature sensor at the airplane cargo hold area is electrically connected with the air conditioner management controller in parallel. According to the scheme, the resistance value of the testing tool equipment is adjusted by adjusting the resistance value of the resistor in the temperature sensor connected in parallel to the airplane cargo compartment area, the resistance value of the resistor connected with the air conditioner controller is changed, then the circuit current value is changed, the environment temperature is changed, and finally the condition that the cargo compartment heating function can be started (the temperature is lower than 10 DEG C) is achieved. And functional verification of the cargo hold heating system is realized.

Description

TECHNICAL FIELD

[0001] The embodiment of the utility model relates to an aircraft cargo compartment heating technical field, especially to an aircraft cargo compartment area heating function opening temperature condition simulation system. BACKGROUND

[0002] Generally, aircraft cargo compartment heating function is set when the temperature of the front cargo compartment area is below 10 DEG C, and the aircraft cargo compartment heating function can be started only by controlling the aircraft cargo compartment heating knob to the "HEAT" position; when the temperature is higher than 10 DEG C, even if the aircraft cargo compartment heating knob is rotated to the "HEAT" position, the cargo compartment heating function will not be started. During the manufacturing process of the aircraft, it is necessary to test whether the cargo compartment heating function is normal, and if the ambient temperature is higher than 10 DEG C, the temperature of the aircraft cargo compartment needs to be reduced to below 10 DEG C to achieve the condition of verifying the cargo compartment heating function.

[0003] At present, when the aircraft is tested for the aircraft cargo compartment heating function, cold air is blown into the aircraft refrigeration area by the refrigeration equipment to reduce the local ambient temperature of the aircraft cargo compartment refrigeration area to below 10 DEG C, so as to realize the function verification of the cargo compartment heating system; since the method of directly blowing in cold air needs a large amount of refrigeration air, and the temperature of the area cannot be quantitatively controlled, it needs to be constantly tried, and after the local temperature of the cargo compartment refrigeration area is reduced, the temperature is unstable, and the temperature of the area cannot be reliably and stably reduced to below 10 DEG C. UTILITY MODEL CONTENT

[0004] The utility model provides a kind of aircraft cargo compartment area heating function opening temperature condition simulation system, the resistance resistance value of test tooling equipment is adjusted by adjusting resistance in parallel to aircraft cargo compartment area place temperature sensor, change the resistance resistance value of air conditioner controller and then change circuit current value, reach the change of ambient temperature, to finally reach the condition that cargo compartment heating function can be enabled (temperature is below 10 DEG C), it is realized that the functionality verification of cargo compartment heating system can be carried out under any temperature condition.

[0005] The utility model embodiment provides a kind of aircraft cargo compartment area heating function opening temperature condition simulation system, and the system includes: resistance adjustment test tooling equipment, aircraft cargo compartment area place temperature sensor and air conditioner management controller;

[0006] The test tooling equipment is electrically connected in parallel with the aircraft cargo compartment area place temperature sensor;The aircraft cargo compartment area place temperature sensor is electrically connected in parallel with the air conditioner management controller.

[0007] Optionally, the resistance adjustment test tooling equipment includes two-way resistance synchronous adjustment box, adapter cable, first electric plug and second electric plug;The adapter cable is connected with the first electric plug, the second electric plug and the two-way resistance synchronous adjustment box respectively;

[0008] The first electric plug is electrically connected with the air-conditioning management controller to connect the two-way resistance synchronous adjustment box with the air-conditioning management controller; and the second electric plug is electrically connected with an electric plug at a temperature sensor far from the aircraft cargo compartment area to connect the two-way resistance synchronous adjustment box with the temperature sensor at the aircraft cargo compartment area.

[0009] The temperature sensor at the aircraft cargo compartment area comprises two PT temperature sensing elements.

[0010] Optionally, the resistance adjustment test tooling device comprises a two-way resistance synchronous adjustment box, an adapter cable, a first electric plug and a second electric plug; the adapter cable is connected with the first electric plug, the second electric plug and the two-way resistance synchronous adjustment box respectively.

[0011] The first electric plug is electrically connected with the temperature sensor at the aircraft cargo compartment area to connect the two-way resistance synchronous adjustment box with the temperature sensor at the aircraft cargo compartment area; and the second electric plug is electrically connected with an electric plug far from the air-conditioning management controller to connect the two-way resistance synchronous adjustment box with the air-conditioning management controller.

[0012] The temperature sensor at the aircraft cargo compartment area comprises two PT temperature sensing elements.

[0013] Optionally, the two-way resistance synchronous adjustment box comprises at least two groups of resistance boxes with different ranges; each of the resistance boxes comprises a resistance box knob disc, a first power supply end, a second power supply end, a first resistance unit and a second resistance unit; the first resistance unit comprises a first resistance, a second resistance, a tenth resistance, and so on.

[0014] The second resistance unit comprises an eleventh resistance, a twelfth resistance, a twentieth resistance, and so on.

[0015] A first end of the resistance box knob disc is electrically connected with a first end of the first resistance.

[0016] A second end of the first resistance is electrically connected with a second end of the resistance box knob disc and a first end of the second resistance; a second end of the second resistance is electrically connected with a third end of the resistance box knob disc; a second end of the second resistance is electrically connected with a first end of the third resistance; a second end of the third resistance is electrically connected with a first end of the fourth resistance and a fourth end of the resistance box knob disc.

[0017] …the second end of the seventh resistor is electrically connected with the eighth end on the resistance box knob disc and the first end of the eighth resistor; the second end of the eighth resistor is electrically connected with the ninth end on the resistance box knob disc; the second end of the eighth resistor is electrically connected with the first end of the ninth resistor; the second end of the ninth resistor is electrically connected with the first end of the tenth resistor and the tenth end on the resistance box knob disc; the second end of the tenth resistor is electrically connected with the eleventh end on the resistance box knob disc and the first power supply end on the second resistance box;

[0018] the twelfth end on the resistance box knob disc is electrically connected with the first end of the eleventh resistor;

[0019] the second end of the eleventh resistor is electrically connected with the thirteenth end on the resistance box knob disc and the first end of the twelfth resistor; the second end of the twelfth resistor is electrically connected with the fourteenth end on the resistance box knob disc; the second end of the twelfth resistor is electrically connected with the first end of the thirteenth resistor; the second end of the thirteenth resistor is electrically connected with the first end of the fourteenth resistor and the fifteenth end on the resistance box knob disc;

[0020] …the second end of the seventeenth resistor is electrically connected with the nineteenth end on the resistance box knob disc and the first end of the eighteenth resistor; the second end of the eighteenth resistor is electrically connected with the twentieth end on the resistance box knob disc; the second end of the eighteenth resistor is electrically connected with the first end of the nineteenth resistor; the second end of the nineteenth resistor is electrically connected with the first end of the twentieth resistor and the twenty first end on the resistance box knob disc; the second end of the twentieth resistor is electrically connected with the twenty second end on the resistance box knob disc and the second power supply end on the second resistance box;

[0021] the first pointer on the resistance box knob disc is adjustably connected with the first end on the resistance box knob disc, …, the eleventh end on the resistance box knob disc; the second pointer on the resistance box knob disc is adjustably connected with the twelfth end on the resistance box knob disc, …, the twenty second end on the resistance box knob disc; the first pointer on the resistance box knob disc is symmetrically arranged with the second pointer on the resistance box knob disc.

[0022] Optionally, the range of the resistance box includes 100K; 10K; 1K; 100Ω; 10Ω; 1Ω.

[0023] Optionally, the resistance value of the temperature sensor at the aircraft cargo area is determined according to different initial temperatures of the aircraft cargo area.

[0024] Optionally, the PT temperature sensing element includes a probe type PT temperature sensing element.

[0025] Optionally, the temperature sensor at the aircraft cargo area is disposed on a line of the aircraft cargo area heating system.

[0026] Optionally, the air conditioning management controller comprises a ventilation controller, a pressure adjustment controller and an anti-icing controller.

[0027] In the embodiment, the resistance adjustment test tool equipment is electrically connected in parallel with the temperature sensor at the aircraft cargo area, and the temperature sensor at the aircraft cargo area is electrically connected in parallel with the air conditioning management controller, so that the resistance value of the resistance adjustment test tool equipment connected in parallel to the temperature sensor at the aircraft cargo area is adjusted, the resistance value connected to the air conditioning controller 30 is changed, the circuit current value is changed, the change of the ambient temperature is achieved, and finally the condition (temperature lower than 10℃) that the cargo compartment heating function can be enabled is achieved, and the functional verification of the cargo compartment heating system is realized. BRIEF DESCRIPTION OF DRAWINGS

[0028] Figure 1 is a structural schematic diagram of an aircraft cargo area heating function opening temperature condition simulation system provided by the embodiment of the utility model;

[0029] Figure 2 is a specific structural schematic diagram of an aircraft cargo area heating function opening temperature condition simulation system provided by the embodiment of the utility model;

[0030] Figure 3 is a connection relationship between the temperature sensor at the aircraft cargo area 20 and the air conditioning management controller in the prior art;

[0031] Figure 4 is a specific structural schematic diagram of another aircraft cargo area heating function opening temperature condition simulation system provided by the embodiment of the utility model;

[0032] Figure 5 is a structural schematic diagram of a two-way resistance synchronous adjustment box provided by the utility model;

[0033] Figure 6 is a structural schematic diagram of a resistance box provided by the utility model. DETAILED DESCRIPTION

[0034] The utility model will be further described in detail in combination with the drawings and embodiments. It can be understood that the specific embodiments described herein are only used to explain the utility model, and not limited to the utility model. In addition, it should be noted that in order to facilitate the description, only the parts related to the utility model are shown in the drawings, not all the structures.

[0035] Figure 1It is a kind of aircraft cargo compartment area heating function opening temperature condition simulation system's structural schematic diagram provided in the embodiment of the utility model, as shown in the figure, the system includes: resistance adjustment test tool equipment 10, aircraft cargo compartment area temperature sensor 20 and air conditioner management controller 30;Resistance adjustment test tool equipment 10 and aircraft cargo compartment area temperature sensor 20 are electrically connected in parallel;Aircraft cargo compartment area temperature sensor 20 and air conditioner management controller 30 are electrically connected in parallel. Figure 1 As shown in the figure, the system includes: resistance adjustment test tool equipment 10, aircraft cargo compartment area temperature sensor 20 and air conditioner management controller 30;Resistance adjustment test tool equipment 10 and aircraft cargo compartment area temperature sensor 20 are electrically connected in parallel;Aircraft cargo compartment area temperature sensor 20 and air conditioner management controller 30 are electrically connected in parallel.

[0036] Among them, resistance adjustment test tool equipment 10 can adjust its internal resistance according to the aircraft cargo compartment area heating function opening temperature condition;Aircraft cargo compartment area temperature sensor 20 is arranged on the pipeline of aircraft cargo compartment area heating system;Aircraft cargo compartment area temperature sensor 20 can measure different initial temperatures at aircraft cargo compartment area when aircraft cargo compartment area heating system starts working or does not start working;That is, the resistance value R1 of aircraft cargo compartment area temperature sensor is determined according to the different initial temperatures of aircraft cargo compartment area.

[0037] Air conditioner management controller 30 can be used as a voltage source, when adjusting the resistance value R2 of resistance adjustment test tool equipment 10, the resistance value (1 / (1 / R2+1 / R1)) after parallel connection of resistance adjustment test tool equipment 10 and aircraft cargo compartment area temperature sensor 20 changes, then aircraft cargo compartment area temperature sensor 20 can also send the resistance value after parallel connection to air conditioner management controller 30, and air conditioner management controller 30 determines the corresponding environmental temperature according to the resistance value after parallel connection.

[0038] In the embodiment, by adjusting the resistance value of resistance adjustment test tool equipment 10 connected in parallel to aircraft cargo compartment area temperature sensor 20, changing the resistance value connected to air conditioner controller 30 and then changing the circuit current value, the environmental temperature is changed, so that the condition (temperature lower than 10℃) that cargo compartment heating function can be enabled is finally reached, and the functional verification of cargo compartment heating system is realized.

[0039] Optionally, on the basis of the above embodiment, the system is further refined, Figure 2 It is a kind of aircraft cargo compartment area heating function opening temperature condition simulation system's specific structural schematic diagram provided in the embodiment of the utility model, as shown in the figure, Figure 2As shown, the resistance adjustment test tool equipment 10 includes two-way resistance synchronous adjustment box 11, adapter cable 12, first electrical plug 13 and second electrical plug 14; the adapter cable 12 is connected with the first electrical plug 13, the second electrical plug 14 and the two-way resistance synchronous adjustment box 11 respectively; the first electrical plug 13 is electrically connected with the air conditioning management controller 30 to connect the two-way resistance synchronous adjustment box 11 with the air conditioning management controller 30; the second electrical plug 14 is electrically connected with the electrical plug B at the temperature sensor 20 far away from the aircraft cargo compartment area to connect the two-way resistance synchronous adjustment box 11 with the temperature sensor 20 at the aircraft cargo compartment area; the temperature sensor 20 at the aircraft cargo compartment area includes two PT temperature sensing elements.

[0040] wherein, Figure 3 is the connection relationship between the temperature sensor 20 at the aircraft cargo compartment area and the air conditioning management controller in the prior art; as Figure 3 As shown, before the functional verification of the cargo compartment heating system, the temperature sensor 20 at the aircraft cargo compartment area is connected with the temperature detection end of the air conditioning controller 30 through the electrical plug A at one end of the wire harness L1, the wire harness L1 and the electrical plug B at the other end of the wire harness; in addition, other detection ends of the air conditioning controller 30 are connected with other detection devices through other electrical plugs C and wire harness L2;

[0041] In actual functional verification of the cargo compartment heating system, the corresponding electrical plugs (electrical plug B and electrical plug C) near the various wire harnesses (such as L1 and L2) at one end of the air conditioning management controller 30 can be disconnected at first, then the electrical plug B of the wire harness L1 corresponding to the temperature detection end of the air conditioning management controller 30 is connected through the second electrical plug 14 on the resistance adjustment test tool equipment 10, and the first electrical plug 13 on the resistance adjustment test tool equipment 10 is connected with the temperature detection end of the air conditioning management controller 30, so that the two-way resistance synchronous adjustment box 11, the air conditioning management controller 30 and the temperature sensor 20 at the aircraft cargo compartment area are electrically connected in parallel two by two, the resistance value of the resistance is adjusted according to the environmental temperature, so as to change the resistance value signal input to the air conditioning management controller 30, so as to simulate the environmental temperature, so that the cargo compartment temperature (temperature lower than 10℃) that can start the cargo compartment heating function is achieved, and the functional verification of the cargo compartment heating system is realized.

[0042] Specifically, since the aircraft cargo compartment area temperature sensor 20 includes two PT temperature sensing elements; the two PT temperature sensing elements are independently arranged; the two-way resistance synchronous adjustment box 11 includes two independently arranged resistors, and the two-way resistance synchronous adjustment box 11 can synchronously adjust the resistance values of the two resistors, so that the two independently arranged resistors are connected in parallel with the two independently arranged PT temperature sensing elements, thereby changing the two independently arranged resistance value signals input to the air conditioner management controller 30, thereby simulating two environment temperatures, and the air conditioner management controller 30 further corrects the two environment temperatures to determine the final simulated environment temperature, so that the cargo compartment heating function can be started (the temperature is lower than 10℃), and the function verification of the cargo compartment heating system is realized; or whether the two environment temperatures are consistent can give an alarm prompt.

[0043] In the above embodiment, after disconnecting the corresponding electrical plug of each line bundle close to one end of the air conditioner management controller 30, the electrical plug C corresponding to the other line bundle needs to be connected with other control subsystem functions (the air conditioner management controller 30 can include a ventilation controller, a pressure adjustment controller and an anti-icing controller; the other control subsystems can include a ventilation system, a pressure adjustment system and an anti-freezing system), and after disassembly, the ventilation, pressure adjustment, anti-icing and other subsystem function tests of the ventilation environmental control system need to be supplemented, so that the aircraft function test efficiency will be affected; in other embodiments, Figure 4 is a specific structural diagram of another aircraft cargo compartment area heating function start temperature condition simulation system provided by the embodiment of the utility model, as shown in Figure 4 The resistance adjustment test tooling equipment 10 includes a two-way resistance synchronous adjustment box 11, a conversion cable 12, a first electrical plug 13 and a second electrical plug 14; the conversion cable 12 is connected with the first electrical plug 13, the second electrical plug 14 and the two-way resistance synchronous adjustment box 11 respectively; the first electrical plug 13 is connected with the aircraft cargo compartment area temperature sensor 20 to connect the two-way resistance synchronous adjustment box 11 with the aircraft cargo compartment area temperature sensor 20; the second electrical plug 14 is connected with the electrical plug A away from the air conditioner management controller 30 to connect the two-way resistance synchronous adjustment box 11 with the air conditioner management controller 30; and the aircraft cargo compartment area temperature sensor 20 includes two PT temperature sensing elements.

[0044] Specifically, in the actual functional verification of the cargo compartment heating system, the electrical plug A at one end of the temperature sensor 20 side wire harness L1 close to the aircraft cargo compartment area can be disconnected, so that the first electrical plug 13 on the resistance adjustment test tool equipment 10 is connected with the temperature sensor 20 at the aircraft cargo compartment area, the second electrical plug 14 on the resistance adjustment test tool equipment 10 is connected with the disconnected electrical plug A, so that the second electrical plug 14 on the resistance adjustment test tool equipment 10 is connected with the air conditioning management controller 30, so that the two-way resistance synchronous adjustment box 11, the air conditioning management controller 30 and the temperature sensor 20 at the aircraft cargo compartment area are electrically connected in parallel in pairs, the two-way resistance synchronous adjustment box 11 adjusts the resistance value of the resistance according to the environmental temperature, so as to change the resistance value signal input to the air conditioning management controller 30, so as to simulate the environmental temperature, so that the cargo compartment temperature (temperature lower than 10℃) that can start the cargo compartment heating function is achieved, and the functional verification of the cargo compartment heating system is realized.

[0045] Specifically, since the aircraft cargo compartment area temperature sensor 20 includes two PT temperature sensing elements, the two PT temperature sensing elements are independently arranged, the two-way resistance synchronous adjustment box 11 includes two independently arranged resistances, and the two-way resistance synchronous adjustment box 11 can synchronously adjust the resistance values of the two resistances, so that the two resistances are electrically connected in parallel with the two independently arranged PT temperature sensing elements, thereby changing the two independent resistance value signals input to the air conditioning management controller 30, so as to simulate two environmental temperatures, and the air conditioning management controller 30 further corrects the two environmental temperatures to determine the final simulated environmental temperature, so that the cargo compartment temperature (temperature lower than 10℃) that can start the cargo compartment heating function is achieved, and the functional verification of the cargo compartment heating system is realized; or whether the two environmental temperatures are consistent can be used to give an alarm prompt.

[0046] In the process of the functional verification of the cargo compartment heating system, the cargo compartment heating knob of the aircraft top control panel is rotated to the "VENT" position, the aircraft cargo compartment area temperature sensor 20 measures the temperature of the cargo compartment ventilation outlet position of the heating system as the initial temperature, and the resistance values of the two-way resistance synchronous adjustment box 11 are adjusted from the maximum value to the resistance value corresponding to the cargo compartment temperature close to the cargo compartment heating function startable temperature, at this time, the simulated environmental temperature is continuously reduced until it is lower than 10℃ which is the cargo compartment heating system startable temperature. Then the cargo compartment ventilation knob of the aircraft top control panel is rotated to "HEAT", and the temperature of the cargo compartment ventilation outlet position is monitored to be obviously higher than the initial temperature, that is, the cargo compartment heating system function is verified to be normal.

[0047] Optionally, Figure 5 is a structural schematic diagram of a two-way resistance synchronous adjustment box provided by the utility model; Figure 6 is a structural schematic diagram of a resistance box provided by the utility model; as Figures 5-6As shown, the two-way resistance synchronous adjustment box 11 includes at least two groups of resistance boxes 111 with different ranges;

[0048] Each resistance box 111 includes a resistance box knob plate F, a first power supply end COM1, a second power supply end COM2, a first resistance unit 1111, and a second resistance unit 1112; the first resistance unit 1111 includes a first resistance R1, a second resistance R2, …, and a tenth resistance R10;

[0049] The second resistance unit 1112 includes an eleventh resistance R11, a twelfth resistance R12, …, and a twentieth resistance R20;

[0050] The first end 10 on the resistance box knob plate F is electrically connected to the first end of the first resistance R1;

[0051] The second end of the first resistance R1 is electrically connected to the second end 9 on the resistance box knob plate and the first end of the second resistance R2; the second end of the second resistance R2 is electrically connected to the third end 8 on the resistance box knob plate; the second end of the second resistance R2 is electrically connected to the first end of the third resistance R3; the second end of the third resistance R3 is electrically connected to the first end of the fourth resistance R4 and the fourth end 7 on the resistance box knob plate;

[0052] …The second end of the seventh resistance R7 is electrically connected to the eighth end 2 on the resistance box knob plate and the first end of the eighth resistance R8; the second end of the eighth resistance R8 is electrically connected to the ninth end 1 on the resistance box knob plate; the second end of the eighth resistance R8 is electrically connected to the first end of the ninth resistance R9; the second end of the ninth resistance R9 is electrically connected to the first end of the tenth resistance R10 and the tenth end 0 on the resistance box knob plate; the second end of the tenth resistance R10 is electrically connected to the eleventh end 0 on the resistance box knob plate and the first power supply end COM1 on the second resistance box;

[0053] The twelfth end 10 on the resistance box knob plate is electrically connected to the first end of the eleventh resistance R11;

[0054] The second end of the eleventh resistance R11 is electrically connected to the thirteenth end 11- on the resistance box knob plate and the first end of the twelfth resistance R12; the second end of the twelfth resistance R12 is electrically connected to the fourteenth end 12- on the resistance box knob plate; the second end of the twelfth resistance R12 is electrically connected to the first end of the thirteenth resistance R13; the second end of the thirteenth resistance R13 is electrically connected to the first end of the fourteenth resistance R14 and the fifteenth end 13- on the resistance box knob plate;

[0055] …the second end of the seventeenth resistor R17 is electrically connected with the nineteenth end 2- on the knob disc of the resistance box and the first end of the eighteenth resistor R18; the second end of the eighteenth resistor R18 is electrically connected with the twentieth end 1- on the knob disc of the resistance box; the second end of the eighteenth resistor R18 is electrically connected with the first end of the nineteenth resistor R19; the second end of the nineteenth resistor R19 is electrically connected with the first end of the twentieth resistor R20 and the twenty-first end 0- on the knob disc of the resistance box; the second end of the twentieth resistor R20 is electrically connected with the twenty-second end 0- on the knob disc of the resistance box and the second power supply end COM2 on the second resistance box;

[0056] the first pointer P1 on the knob disc of the resistance box is adjustably connected with the first end 1 on the knob disc of the resistance box, …, the eleventh end 0 on the knob disc of the resistance box; the second pointer P2 on the knob disc of the resistance box is adjustably connected with the twelfth end 10- on the knob disc of the resistance box, …, the twenty-second end 0- on the knob disc of the resistance box. The first pointer P1 on the knob disc of the resistance box is symmetrically arranged with the second pointer P2 on the knob disc of the resistance box.

[0057] The first resistance unit and the second resistance unit on each resistance box 111 on the two-way resistance synchronous adjustment box 11 can realize synchronous resistance adjustment, that is, the resistance value of the first resistance unit and the resistance value of the second resistance unit can be adjusted to be the same. Specifically, there are two pointers on the knob disc of the resistance box. When the two pointers rotate simultaneously, the two pointers are respectively connected with two independent resistances, the resistance values of the two resistances are the same, and the two-way resistance synchronous adjustment box 11 can control the size of the resistance value of each group of resistances into the circuit. It can be understood that the resistance values of the two circuits into which the two pointers are connected at any position are equal. The two resistances are connected in parallel with two independent two-way PT temperature sensing elements through four connection points A, B, D and E.

[0058] The resistance value of one of the two resistances is determined as follows. If one pointer contacts the second end (corresponding to 9 on the left side in the figure) on the knob disc of the resistance box, the resistance value of this path is the sum of the first resistance, the second resistance, …, the ninth resistance in series. Since each resistance is the same, the resistance value of this path is 9*resistance range.

[0059] Similarly, if one pointer contacts the second end (corresponding to 9 on the left side in the figure) on the knob disc of the resistance box, the other contact contacts the twenty-first end (corresponding to 19 on the right side in the figure) on the knob disc of the resistance box. Then the resistance value of this path is the sum of the eleventh resistance, the twelfth resistance, …, the nineteenth resistance in series. Since each resistance is the same, the resistance value of this path is 9*resistance range. In this way, the resistance values of the two resistances are adjusted to be the same.

[0060] It can be understood that the range of the resistance box includes 100K; 10K; 1K; 100Ω; 10Ω; 1Ω; the embodiment is not limited to this; in addition, the number of the resistance box in the two-way resistance synchronous adjusting box 11 is not limited in the embodiment, which can be determined according to the cargo hold temperature that can enable the cargo hold heating function to start.

[0061] It should be noted that the above are only preferred embodiments of the present application and the technical principles applied. Those skilled in the art will understand that the present application is not limited to the specific embodiments described herein, and those skilled in the art can make various obvious changes, re-adjustments and substitutions without departing from the scope of the present application. Therefore, although the present application has been described in more detail through the above embodiments, the present application is not limited to the above embodiments, and can include more other equivalent embodiments without departing from the concept of the present application, and the scope of the present application is determined by the scope of the appended claims.

Claims

1. An aircraft cargo compartment area heating function on temperature condition simulation system, characterized by, The application relates to an aircraft cargo compartment temperature sensor and an air conditioner management controller, and relates to an aircraft cargo compartment temperature sensor and an air conditioner management controller. The resistance adjustment test tool equipment is electrically connected in parallel with the aircraft cargo compartment temperature sensor, and the aircraft cargo compartment temperature sensor is electrically connected in parallel with the air conditioner management controller.

2. The aircraft cargo compartment area heating function on temperature condition simulation system of claim 1, wherein, The resistance adjustment test tool equipment comprises two-way resistance synchronous adjustment boxes, an adapter cable, a first electric plug and a second electric plug; the adapter cable is connected with the first electric plug, the second electric plug and the two-way resistance synchronous adjustment boxes respectively; The first electric plug is electrically connected with the air conditioner management controller so as to connect the two-way resistance synchronous adjustment boxes with the air conditioner management controller; the second electric plug is electrically connected with an electric plug away from the aircraft cargo compartment temperature sensor so as to connect the two-way resistance synchronous adjustment boxes with the aircraft cargo compartment temperature sensor; The aircraft cargo compartment temperature sensor comprises two PT temperature sensing elements.

3. The aircraft cargo compartment area heating function on temperature condition simulation system of claim 1, wherein, The resistance adjustment test tool equipment comprises two-way resistance synchronous adjustment boxes, an adapter cable, a first electric plug and a second electric plug; the adapter cable is connected with the first electric plug, the second electric plug and the two-way resistance synchronous adjustment boxes respectively; The first electric plug is electrically connected with the aircraft cargo compartment temperature sensor so as to connect the two-way resistance synchronous adjustment boxes with the aircraft cargo compartment temperature sensor; the second electric plug is electrically connected with an electric plug away from the air conditioner management controller so as to connect the two-way resistance synchronous adjustment boxes with the air conditioner management controller; The aircraft cargo compartment temperature sensor comprises two PT temperature sensing elements.

4. The aircraft cargo compartment area heating function on temperature condition simulation system according to claim 2 or 3, characterized in that, The two-way resistance synchronous adjustment boxes comprise at least two groups of resistance boxes with different scales; Each resistance box comprises a resistance box knob disc, a first power supply end, a second power supply end, a first resistance unit and a second resistance unit; the first resistance unit comprises a first resistance, a second resistance, a tenth resistance; the second resistance unit comprises an eleventh resistance, a twelfth resistance, a twentieth resistance; A first end on the resistance box knob disc is electrically connected with a first end of the first resistance; A second end of the first resistance is electrically connected with a second end on the resistance box knob disc and a first end of the second resistance; a second end of the second resistance is electrically connected with a third end on the resistance box knob disc; a second end of the second resistance is electrically connected with a first end of the third resistance; a second end of the third resistance is electrically connected with a first end of the fourth resistance and a fourth end on the resistance box knob disc; A second end of the seventh resistance is electrically connected with an eighth end on the resistance box knob disc and a first end of the eighth resistance; a second end of the eighth resistance is electrically connected with a ninth end on the resistance box knob disc; a second end of the eighth resistance is electrically connected with a first end of the ninth resistance; a second end of the ninth resistance is electrically connected with a first end of the tenth resistance and a tenth end on the resistance box knob disc; a second end of the tenth resistance is electrically connected with an eleventh end on the resistance box knob disc and a first power supply end on the second resistance box; The twelfth end on the resistance box knob disc is electrically connected with the first end of the eleventh resistance; The second end of the eleventh resistance is electrically connected with the thirteenth end on the resistance box knob disc and the first end of the twelfth resistance; the second end of the twelfth resistance is electrically connected with the fourteenth end on the resistance box knob disc; the second end of the twelfth resistance is electrically connected with the first end of the thirteenth resistance; the second end of the thirteenth resistance is electrically connected with the first end of the fourteenth resistance and the fifteenth end on the resistance box knob disc; The second end of the seventeenth resistance is electrically connected with the nineteenth end on the resistance box knob disc and the first end of the eighteenth resistance; the second end of the eighteenth resistance is electrically connected with the twentieth end on the resistance box knob disc; the second end of the eighteenth resistance is electrically connected with the first end of the nineteenth resistance; the second end of the nineteenth resistance is electrically connected with the first end of the twentieth resistance and the twenty-first end on the resistance box knob disc; the second end of the twentieth resistance is electrically connected with the twenty-second end on the resistance box knob disc and the second power supply end on the second resistance box; The first pointer on the resistance box knob disc is adjustably connected with the first end on the resistance box knob disc, the eleventh end on the resistance box knob disc; the second pointer on the resistance box knob disc is adjustably connected with the twelfth end on the resistance box knob disc, the twenty-second end on the resistance box knob disc; the first pointer on the resistance box knob disc is symmetrically arranged with the second pointer on the resistance box knob disc.

5. The aircraft cargo compartment area heating function on temperature condition simulation system of claim 4, wherein, The range of the resistance box includes 100K; 10K; 1K; 100Ω; 10Ω; 1Ω.

6. The aircraft cargo compartment area heating function on temperature condition simulation system of claim 1, wherein, The resistance value of the temperature sensor at the aircraft cargo area is determined according to different initial temperatures of the aircraft cargo area.

7. The aircraft cargo compartment area heating function on temperature condition simulation system according to claim 2 or 3, characterized in that, The PT temperature sensing element includes a probe-in type PT temperature sensing element.

8. The aircraft cargo bay area heating function on temperature condition simulation system of claim 1, wherein, The temperature sensor at the aircraft cargo area is arranged on a pipeline of the aircraft cargo area heating system.

9. The aircraft cargo bay area heating function on temperature condition simulation system of claim 1, wherein, The air conditioner management controller includes a ventilation controller, a pressure adjustment controller and an anti-icing controller.

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