Aircraft external temperature indication system

Abstract

This invention discloses an aircraft external ambient temperature indication system and an aircraft external ambient temperature indication component. The aircraft external ambient temperature indication system includes an input module comprising: a temperature acquisition module, an air pressure and altitude acquisition module, a temperature envelope database, and an operating mode switching module; a data processing module comprising: a data storage module, which stores the input external ambient temperature, external air pressure and altitude, and temperature envelope data as reference data; a data calculation module, which calculates the reference data to obtain the instantaneous temperature boundary and calculates the absolute value of the difference between the external ambient temperature and the instantaneous temperature boundary; and an output module comprising: a display module and an alarm module. The aircraft external ambient temperature indication component includes a first boundary and a second boundary of the scale portion, determined by the instantaneous temperature boundary, and multiple scales of the scale portion are set in a linear distribution according to the values ​​of the temperature boundaries corresponding to the first and second boundaries.

Description

Technical Field

[0001] This invention relates to an aircraft external ambient temperature indication system and an aircraft external ambient temperature indication component for the system, specifically, to an external ambient temperature indication component for an aircraft cockpit display. This technical solution belongs to the field of avionics equipment. Background Technology

[0002] During flight, the ambient temperature outside the aircraft varies with its altitude and speed. High and low temperatures are environments that aircraft may encounter during operation. In extreme cases, these conditions can severely impact various components and systems of the aircraft, imposing various limitations and affecting its normal use.

[0003] In the prior art, the methods for indicating the external ambient temperature of an aircraft are mainly as follows: 1) displaying several items in the form of pure numerical values, such as that disclosed in CN108557091A; 2) a sign (indicating the items displayed) + numerical value.

[0004] However, existing solutions only provide the aircraft's current external temperature value, but cannot provide aircraft users, such as flight crews, maintenance personnel, and ground test personnel, with the boundary range of the aircraft's temperature envelope and a comparison between the external temperature value and the temperature envelope.

[0005] The aircraft temperature envelope, as one of the aircraft envelopes, is an important indicator affecting aircraft safety. It reflects the aircraft's ability to withstand the range of external ambient temperatures during operation and can fully reflect the limitations of aircraft pressure, altitude, and temperature.

[0006] Therefore, there remains a need for further improvements to the structure of existing aircraft external ambient temperature indication components. Summary of the Invention

[0007] In view of the above-mentioned problems in the prior art, the purpose of the present invention is to provide an aircraft external ambient temperature indication system, which includes a display module, so that aircraft operators can refer to the aircraft temperature envelope to more intuitively, conveniently and comprehensively grasp the aircraft's external temperature information.

[0008] To address the aforementioned problems, this invention provides an aircraft external ambient temperature indication system, comprising: an input module, which includes: a temperature acquisition module for acquiring the external ambient temperature corresponding to the aircraft's exterior; a barometric altitude acquisition module for acquiring the current barometric altitude outside the aircraft; a temperature envelope database for providing temperature envelope data corresponding to the aircraft model; a working mode switching module for selectively switching the aircraft external ambient temperature indication system to operate in either Celsius or Fahrenheit modes; and a data processing module that is electrically connected to the input module and includes: a data storage... The system comprises: a storage module that stores the input ambient temperature, ambient pressure altitude, and temperature envelope data as reference data; a data calculation module that calculates the reference data to obtain the instantaneous temperature boundary and calculates the absolute value of the difference between the ambient temperature and the instantaneous temperature boundary; an output module that displays the ambient temperature and the instantaneous temperature boundary; and an alarm module that issues an alarm upon receiving an alarm signal from the data calculation module. Specifically, if the absolute value of the difference between the ambient temperature and the instantaneous temperature boundary falls within a first temperature range, the data calculation module sends an alarm signal to the output module.

[0009] According to one aspect of the invention, in the data calculation module, if the absolute value of the difference between the external ambient temperature and the instantaneous temperature boundary exceeds the range of a first temperature range and falls within the range of the first temperature range plus a second temperature, a warning signal is sent to the output module, thereby triggering a warning alarm from the alarm module.

[0010] According to one aspect of the present invention, a display module includes an aircraft external ambient temperature indicating component, comprising: an instrument panel; a label disposed on the instrument panel; a scale portion disposed on the instrument panel, the scale portion including a plurality of scales and a plurality of scale indicators, the scale portion including a first boundary and a second boundary at both ends; and an indicating portion disposed on the instrument panel, and indicating the measured external ambient temperature based on the scale of the scale portion, characterized in that the first boundary and the second boundary of the scale portion are determined by an instantaneous temperature boundary from a data calculation module of the aircraft external ambient temperature indicating system according to the present invention, and the plurality of scales of the scale portion are set in a linear distribution according to the values ​​of the temperature boundaries corresponding to the first boundary and the second boundary.

[0011] According to one aspect of the present invention, the scale portion includes two over-limit alarm indication portions and two over-limit warning indication portions, the two over-limit alarm indication portions being adjacent to the first boundary and the second boundary respectively, and the two over-limit warning indication portions being adjacent to the corresponding over-limit alarm indication portions respectively.

[0012] According to one aspect of the invention, the temperature range indicated by the over-limit alarm indication portion is the first temperature range of the alarm module of the system according to the invention, and in the scale portion, the over-limit alarm indication portion is within the range of the first boundary to the first boundary plus the first temperature range, and within the range of the second boundary minus the first temperature range to the second boundary.

[0013] According to one aspect of the invention, the temperature range indicated by the over-limit warning indication portion is a second temperature range, and in the scale portion, the over-limit warning indication portion is within the range of the first boundary plus the first temperature range to the first boundary plus the first temperature range plus the second temperature range, and within the range of the second boundary minus the first temperature range minus the second temperature range to the second boundary minus the first temperature range.

[0014] According to one aspect of the invention, a first portion of a plurality of scale indicators of the scale portion displays "-" when the ambient temperature indicated by the corresponding scale indicator is below 0 degrees, and does not display when the ambient temperature indicated by the corresponding scale indicator is above 0 degrees; and a second portion of the plurality of scale indicators of the scale portion displays the corresponding integer temperature scale value with an accuracy of 10 degrees.

[0015] According to one aspect of the invention, the instrument panel further includes an instant temperature display portion, wherein a first portion of the instant temperature display portion displays "-" when the ambient temperature is below 0 degrees and does not display when the ambient temperature is above 0 degrees, wherein a second portion of the instant temperature display portion displays the corresponding instant temperature with an accuracy of 1 degree or 0.5 degrees, and wherein a third portion of the instant temperature display portion displays the temperature unit of Celsius or Fahrenheit.

[0016] According to one aspect of the invention, the instrument panel is in the form of a semi-circular dial; the scale portion is located adjacent to the arcuate portion of the instrument panel; and the indicator portion is in the form of a pointer.

[0017] According to one aspect of the invention, the instrument panel is rectangular and straight; the scale portion is in the form of a strip and is disposed in the middle of the instrument panel; and the indicator portion is in the form of a rectangular frame, wherein the first and second portions of the indicator portion are in the same format as the scale indicator.

[0018] Compared with the prior art, the aircraft external ambient temperature indication system and aircraft external ambient temperature indication component of the present invention use a graphical envelope boundary to make an intuitive comparison with the aircraft external ambient temperature, so that aircraft users can more intuitively, conveniently and comprehensively grasp the aircraft external temperature information by referring to the aircraft temperature envelope. Attached Figure Description

[0019] To gain a more complete understanding of the invention, reference can be made to the following description of exemplary embodiments taken in conjunction with the accompanying drawings. The drawings are schematic and not necessarily drawn to scale, but are intended to illustrate the invention more clearly. In the drawings:

[0020] Figure 1 This is a schematic diagram of an aircraft external ambient temperature indication system according to an embodiment of the present invention.

[0021] Figure 2 This is a schematic diagram of an aircraft external ambient temperature indication component according to an embodiment of the present invention.

[0022] Figure 3 yes Figure 2 A schematic diagram showing the external ambient temperature indicator component of an aircraft indicating that the external ambient temperature is approaching the first boundary.

[0023] Figure 4 yes Figure 2 A schematic diagram of an aircraft external ambient temperature indicator component indicating that the external ambient temperature is approaching the second boundary.

[0024] Figure 5 This is a schematic diagram of an aircraft external ambient temperature indication component according to another embodiment of the present invention.

[0025] List of reference numerals in the attached diagram:

[0026] 10 Input Module

[0027] 11 Temperature Acquisition Module

[0028] 12 Barometric Altitude Acquisition Module

[0029] 13 Temperature Envelope Database

[0030] 14 Working Mode Switching Module

[0031] 20 Data Processing Module

[0032] 21 Data storage module

[0033] 22 Data Calculation Module

[0034] 30 Output Module

[0035] 31 Display Module

[0036] 32 Alarm Module

[0037] 40 signs

[0038] 50 Instrument Panel

[0039] 60 scale section

[0040] 61 First Boundary

[0041] 62 Second Boundary

[0042] 63 Over-limit alarm indication section

[0043] 64 Over-limit warning instruction section

[0044] 70 Indicator Section

[0045] 80 Real-time temperature display section

[0046] Δ1 First temperature range

[0047] Δ2 Second temperature range Detailed Implementation

[0048] The present invention will be further described below with reference to specific embodiments and accompanying drawings. More details are set forth in the following description in order to provide a full understanding of the present invention. However, the present invention can obviously be implemented in many other ways different from those described herein. Those skilled in the art can make similar extensions and derivations based on actual application situations without departing from the spirit of the present invention. Therefore, the scope of protection of the present invention should not be limited by the content of this specific embodiment.

[0049] Figure 1 An embodiment of the present invention is illustrated in the diagram of an aircraft external ambient temperature indication system, which includes an input module 10 for collecting atmospheric environment data and loading a temperature envelope database, a data processing module 20 for electrically communicating with the input module 10, and an output module 3 for providing processing results.

[0050] In a preferred embodiment, the input module 10 may include a temperature acquisition module 11, a barometric altitude acquisition module 12, and a temperature envelope database 13. The temperature acquisition module 11 can acquire the ambient temperature corresponding to the aircraft's external atmospheric environment, while the barometric altitude acquisition module 12 can acquire the aircraft's current barometric altitude. The temperature envelope database 13 can serve as a data source for the aircraft's operating temperature envelope. When needed, temperature envelope data curves are read from the database to provide temperature envelope data corresponding to the aircraft model. The temperature envelope is related to the aircraft's barometric altitude; the current barometric altitude of the aircraft is calculated through external atmospheric static pressure and used as input data.

[0051] Preferably, the input module 10 may also have a working mode switching module 14, which can selectively switch the aircraft external ambient temperature indication system according to the present invention to operate in Celsius or Fahrenheit mode, and correspondingly switch the working modes of the temperature acquisition module 11, the barometric altitude acquisition module 12 and the temperature envelope database 13.

[0052] In a preferred embodiment, simultaneously, the data processing module 20, which is electrically in communication with the input module 10, stores and calculates the collected ambient temperature, external air pressure altitude, and temperature envelope data as reference data to obtain the instantaneous temperature boundary. The data processing module 20 may have a data storage module 21 and a data calculation module 22. The data storage module 21 stores the input ambient temperature, external air pressure altitude, and temperature envelope data as reference data, while the data calculation module 22 calculates the stored reference data to obtain the instantaneous temperature boundary.

[0053] In a preferred embodiment, the data calculation module 22 of the aircraft external ambient temperature indication system according to the present invention can further calculate the absolute value of the difference between the external ambient temperature and the instantaneous temperature boundary, and send different output signals to the output module 30 according to the absolute value of the difference between the external ambient temperature and the instantaneous temperature boundary. Here, the difference between the current temperature and the temperature envelope boundary should be determined using the absolute value of the difference, taking into account both the left and right boundaries. Further details regarding the output module 30 will be provided below.

[0054] Preferably, if the absolute value of the difference between the external ambient temperature and the instantaneous temperature boundary is within the first temperature range Δ1, an alarm signal is sent to the output module 30, thereby prompting the alarm module 32 to issue a warning alarm.

[0055] Preferably, if the absolute value of the difference between the external ambient temperature and the instantaneous temperature boundary exceeds the range of the first temperature range Δ1 and is within the range of the first temperature range Δ1 plus the second temperature Δ2, a warning signal is sent to the output module 30, thereby the alarm module 32 issues a warning alarm.

[0056] Refer again Figure 1 The aircraft external ambient temperature indication system according to the present invention may further include an output module 30 for providing the crew with the processing conclusions and further information of the data processing module 20.

[0057] In a preferred embodiment, the output module 30 may include a display module 31 and an alarm module 32 as described above. The display module 31 can provide the crew with information such as text and images to display the external ambient temperature and the real-time temperature boundary. After receiving the output signal from the data calculation module 22, the alarm module 32 can issue an alarm to the crew through images, lights, sounds, vibrations, etc.

[0058] In a preferred embodiment, the display module 31 may include an aircraft external ambient temperature indication component according to the present invention, which will be described in detail below.

[0059] Now go to Figure 2The image schematically illustrates an aircraft external ambient temperature indicator assembly according to an embodiment of the present invention, which has an instrument panel 50 as a base plate, a nameplate 40 indicating what parameter the aircraft external ambient temperature indicator assembly according to the present invention indicates, a scale portion 60 indicating the temperature, and an indicator 70 indicating the real-time external ambient temperature.

[0060] In one embodiment, such as Figure 2 The aircraft external ambient temperature indicator shown is in the form of rectangular bars. It should be understood that this indicator is not limited to a bar arrangement and may also take other forms, such as those described in detail below. Figure 5 The pointer dial or other display formats that meet the display requirements.

[0061] In one embodiment, the instrument panel 50 has multiple scale markings on the scale portion 60, and multiple scale indicators represent the temperature indicated at the corresponding position.

[0062] Preferably, the scale portion 60 is in the form of a strip and is located in the center of the instrument panel 50. The scale portion 60 further includes a first boundary 61 and a second boundary 62 at both ends of the strip. The first boundary 61 and the second boundary 62 of the scale portion 60 can be determined by real-time temperature boundaries from the data calculation module 22 based on the aircraft external ambient temperature indication system described above. Furthermore, the multiple scales of the scale portion 60 can be set in a linear distribution based on the values ​​of the temperature boundaries corresponding to the first boundary 61 and the second boundary 62.

[0063] Preferably, the first portion of the plurality of scale indicators in the scale portion 60 displays a "-" (negative sign) when the corresponding ambient temperature indicated by the scale indicator is below 0 degrees Celsius, and does not display a negative sign when the corresponding ambient temperature indicated by the scale indicator is above 0 degrees Celsius. Preferably, the first portion of the scale indicator is displayed in white. Furthermore, the second portion of the plurality of scale indicators in the scale portion 60 can display the corresponding integer temperature scale value with an accuracy of 10 degrees Celsius. Preferably, the second portion of the scale indicator is displayed in white.

[0064] In one embodiment, the instrument panel 50 includes an indicator portion 70, for example, in the form of a rectangular frame, and the indicator portion 70 indicates the measured ambient temperature based on the scale of the scale portion 60. Preferably, the first and second portions of the indicator portion 70 are in the same format as the scale indicator. Preferably, the indicator portion 70 is displayed in green.

[0065] In one embodiment, the instrument panel 50 may also have a label 40 on the left side of the scale portion 60 to indicate what parameters the aircraft external ambient temperature indication component according to the invention indicates, such as total temperature (TAT) and static temperature (SAT). Preferably, the label 40 is displayed in green.

[0066] In one embodiment, the instrument panel 50 may also have an instantaneous temperature display section 80 on the right side of the scale section 60 to display the measured ambient temperature. Preferably, the first part of the instantaneous temperature display section 80 displays "-" when the ambient temperature is below 0 degrees Celsius, and does not display anything when the ambient temperature is above 0 degrees Celsius. Preferably, the second part of the instantaneous temperature display section 80 displays the instantaneous temperature corresponding to the aircraft's ambient temperature, indicating an accuracy of 0.5 when using the "XX.X" format and an accuracy of 1 when using the "XX" format. The accuracy is 1 degree or 0.5 degrees Celsius. Preferably, depending on the operating mode selected by the operating mode switching module 14 of the above-mentioned aircraft ambient temperature indication system (either Celsius or Fahrenheit), the third part of the instantaneous temperature display section 80 displays the temperature unit in Celsius or Fahrenheit. Preferably, the instantaneous temperature display section 80 displays green.

[0067] Figure 3 schematically shown Figure 2 The aircraft external ambient temperature indicator component indicates that the indicated external ambient temperature is close to the first boundary 61. Figure 4 schematically shown Figure 2 The aircraft external ambient temperature indication component indicates an ambient temperature close to a second boundary 62. Preferably, the scale portion 60 may include two over-limit warning indication portions 63 and two over-limit early warning indication portions 64. The two over-limit warning indication portions 63 are respectively adjacent to the first boundary 61 and the second boundary 62, and the two over-limit early warning indication portions 64 are respectively adjacent to their corresponding over-limit warning indication portions 63. Preferably, the over-limit warning indication portions 63 are represented by a red stripe covering a portion of the scale portion 60. Preferably, the over-limit early warning indication portions 64 are represented by a yellow stripe covering a portion of the scale portion 60.

[0068] In one embodiment, the temperature range indicated by the over-limit alarm indication portion 63 is a first temperature range Δ1. Specifically, in the scale portion 60, the over-limit alarm indication portion 63 indicates a range of (first boundary 61, first boundary 61 + Δ1) and (second boundary 62 - Δ1, second boundary 62); that is, the over-limit alarm indication portion 63 is within the range of the first boundary 61 to the first boundary 61 plus the first temperature range Δ1, and within the range of the second boundary 62 minus the first temperature range Δ1 to the second boundary 62.

[0069] In one embodiment, the temperature range indicated by the over-limit warning indication portion 64 is the second temperature range Δ2. Specifically, in the scale portion 60, the over-limit warning indication portion 64 indicates a range of (first boundary 61 + Δ1, first boundary 61 + Δ1 + Δ2) and (second boundary 62 - Δ1 - Δ2, second boundary 62 - Δ1); that is, the over-limit warning indication portion 64 is within the range of the first boundary 61 plus the first temperature range Δ1 to the first boundary 61 plus the first temperature range Δ1 plus the second temperature range Δ2, and within the range of the second boundary 62 minus the first temperature range Δ1 minus the second temperature range Δ2 to the second boundary 62 minus the first temperature range Δ1.

[0070] Figure 5 A schematic diagram of an aircraft external ambient temperature indication component according to another embodiment of the present invention is shown. Thus, the previously described components are similarly numbered in this figure.

[0071] In this embodiment, the instrument panel 50 of the aircraft external ambient temperature indicator component is in the form of a semi-circular dial. Preferably, the scale portion 60 is located adjacent to the arcuate portion of the instrument panel 50. Preferably, the indicator portion 70 is in the form of a pointer. Preferably, the label 40 and the real-time temperature display portion 80 are located at the center of the semicircle of the instrument panel 50.

[0072] Although various embodiments have been described above, it should be understood that they are presented by way of example and not limitation. It will be apparent to those skilled in the art that the disclosed subject matter may be implemented in other specific forms without departing from its spirit and essential characteristics. Therefore, the embodiments described above are to be considered exemplary in all respects and not as limiting of the invention.

Claims

1. An aircraft external ambient temperature indication system, characterized in that, The aircraft external ambient temperature indication system includes: Input module (10), the input module (10) having: Temperature acquisition module (11), wherein the temperature acquisition module (11) acquires the external ambient temperature corresponding to the outside of the aircraft; The barometric altitude acquisition module (12) acquires the external barometric altitude corresponding to the outside of the aircraft. Temperature envelope database (13), which provides temperature envelope data corresponding to the aircraft model; Operating mode switching module (14), which selectively switches the aircraft external ambient temperature indication system to operate in Celsius or Fahrenheit mode; and A data processing module (20) that is in electrical communication with the input module (10), and the data processing module (20) having: The data storage module (21) stores the input external ambient temperature, external air pressure altitude and temperature envelope data as reference data respectively. The data calculation module (22) calculates the reference data to obtain the instantaneous temperature boundary, and calculates the absolute value of the difference between the external ambient temperature and the instantaneous temperature boundary; and Output module (30), the output module (30) having: Display module (31), the display module (31) displays the external ambient temperature and the instantaneous temperature boundary; and An alarm module (32) issues an alarm after receiving an alarm signal from the data calculation module (22). In the data calculation module (22), if the absolute value of the difference between the external ambient temperature and the instantaneous temperature boundary is within the first temperature range (Δ1), the alarm signal is sent to the output module (30).

2. The aircraft external ambient temperature indication system according to claim 1, characterized in that, In the data calculation module (22), if the absolute value of the difference between the external ambient temperature and the instantaneous temperature boundary exceeds the range of the first temperature range (Δ1) and is within the first temperature range (Δ1) plus the second temperature range (Δ2), then a warning signal is sent to the output module (30), thereby the alarm module (32) issues a warning alarm.

3. The aircraft external ambient temperature indication system according to claim 2, characterized in that, The display module includes an aircraft external ambient temperature indicator component, the aircraft external ambient temperature indicator component comprising: Instrument panel (50); A sign (40) is provided on the instrument panel (50); A scale portion (60) is disposed on the instrument panel (50), the scale portion (60) including multiple scales and multiple scale indicators, the scale portion (60) including a first boundary (61) and a second boundary (62) at both ends; and An indicator portion (70) is provided on the instrument panel (50) and indicates the measured external ambient temperature based on the scale of the scale portion (60). in, The first boundary (61) and the second boundary (62) of the scale portion (60) are determined by the instantaneous temperature boundary from the data calculation module (22) of the aircraft external ambient temperature indication system according to claim 2, and the plurality of scales of the scale portion (60) are set in a linear distribution according to the values ​​of the temperature boundaries corresponding to the first boundary (61) and the second boundary (62).

4. The aircraft external ambient temperature indication system according to claim 3, characterized in that, The scale portion (60) includes two over-limit alarm indication portions (63) and two over-limit warning indication portions (64). The two over-limit alarm indication portions (63) are respectively adjacent to the first boundary (61) and the second boundary (62), and the two over-limit warning indication portions (64) are respectively adjacent to the corresponding over-limit alarm indication portions (63).

5. The aircraft external ambient temperature indication system according to claim 4, characterized in that, The temperature range indicated by the over-limit alarm indication section (63) is the first temperature range (Δ1) of the alarm module (32) of the system according to claim 2, and In the scale portion (60), the over-limit alarm indication portion (63) is within the range from the first boundary (61) to the first boundary (61) plus the first temperature range (Δ1), and within the range from the second boundary (62) minus the first temperature range (Δ1) to the second boundary (62).

6. The aircraft external ambient temperature indication system according to claim 4, characterized in that, The temperature range indicated by the over-limit warning indication section (64) is the second temperature range (Δ2), and In the scale portion (60), the over-limit warning indication portion (64) is within the range of the first boundary (61) plus the first temperature range (Δ1) to the first boundary (61) plus the first temperature range (Δ1) plus the second temperature range (Δ2), and within the range of the second boundary (62) minus the first temperature range (Δ1) minus the second temperature range (Δ2) to the second boundary (62) minus the first temperature range (Δ1).

7. The aircraft external ambient temperature indication system according to claim 3, characterized in that, The first portion of the plurality of scale indicators of the scale portion (60) displays "-" when the corresponding ambient temperature indicated by the scale indicator is below 0 degrees, and does not display when the corresponding ambient temperature indicated by the scale indicator is above 0 degrees. The second part of the multiple scale indicators of the scale section (60) displays the corresponding integer temperature scale value with an accuracy of 10 degrees.

8. The aircraft external ambient temperature indication system according to claim 3, characterized in that, The instrument panel (50) also includes a real-time temperature display section (80). The first part of the real-time temperature display section (80) displays "-" when the external ambient temperature is below 0 degrees Celsius, and does not display anything when the external ambient temperature is above 0 degrees Celsius. The second part of the real-time temperature display section (80) displays the corresponding real-time temperature with an accuracy of 1 degree or 0.5 degrees. The third part of the instant temperature display section (80) displays the temperature unit in Celsius or Fahrenheit.

9. The aircraft external ambient temperature indication system according to claim 3, characterized in that, The instrument panel (50) is in the form of a semi-circular dial; The scale portion (60) is positioned adjacent to the arcuate portion of the instrument panel (50); and The indicator part (70) is in the form of a pointer.

10. The aircraft external ambient temperature indication system according to claim 3, characterized in that, The instrument panel (50) is rectangular with straight bars; The scale portion (60) is in the form of a strip and is located in the center of the instrument panel (50); and The indicator portion (70) is in the form of a rectangle, and the first and second portions of the indicator portion (70) are in the same format as the scale indicator.

Images