CN216593526U - Novel dual-redundancy atmospheric data system - Google Patents
Novel dual-redundancy atmospheric data system Download PDFInfo
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- CN216593526U CN216593526U CN202122064862.9U CN202122064862U CN216593526U CN 216593526 U CN216593526 U CN 216593526U CN 202122064862 U CN202122064862 U CN 202122064862U CN 216593526 U CN216593526 U CN 216593526U
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Abstract
The utility model discloses a novel dual-redundancy atmospheric data system which comprises a nose airspeed head, a field-pressure binding device, a total temperature sensor, a first atmospheric data reference unit and a second atmospheric data reference unit, wherein the output ends of the total temperature sensor and the field-pressure binding device are respectively connected with the first atmospheric data reference unit and the second atmospheric data reference unit. The atmospheric data reference unit calculates atmospheric parameters such as air pressure height, rising speed, corrected airspeed, vacuum speed, Mach number, attack angle, sideslip angle, atmospheric static temperature, atmospheric air density ratio and the like according to a navigation mark standard according to a received aircraft nose airspeed head pipe attack angle signal and sideslip angle signal, a total pressure digital signal calculated by an atmospheric data module, a static pressure digital signal calculated by the atmospheric data module, a total temperature resistance signal of a total temperature sensor and a field pressure signal of a field pressure fastener. The utility model constructs an independent dual-redundancy atmospheric data system and ensures the requirements of high reliability and high safety of the atmospheric data system.
Description
Technical Field
The utility model belongs to the technical field of measurement and calibration of airplane atmospheric data, and particularly relates to a novel dual-redundancy atmospheric data system.
Background
The atmospheric data system provides a large amount of accurate information, such as barometric altitude, rising speed, corrected airspeed, vacuum speed, Mach number, angle of attack, sideslip angle, atmospheric static temperature and large air density ratio, is of great importance to ensuring flight safety, and is also information required by a plurality of key avionic subsystems for ensuring that pilots execute flight tasks. Thus, on all modern civil and military aircraft, the air data system itself is one of the key avionics systems, and is also an indispensable core element of other avionics subsystems.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a novel dual-redundancy atmospheric data system, and aims to solve the problems that the conventional atmospheric data system is greatly interfered by a machine body, has a large gas circuit hysteresis effect and is difficult to correct.
The utility model is mainly realized by the following technical scheme:
a novel dual-redundancy atmospheric data system comprises a nose airspeed head, a field-pressure binding device and a total temperature sensor, wherein the nose airspeed head is respectively connected with a first three-way gas path switching unit and a second three-way gas path switching unit through a static pressure gas path pipeline and a total pressure gas path pipeline; the first static pressure atmospheric data module and the first total pressure atmospheric data module respectively output static pressure digital signals and total pressure digital signals to be connected with the first atmospheric data reference unit, and the second static pressure atmospheric data module and the second total pressure atmospheric data module respectively output static pressure digital signals and total pressure digital signals to be connected with the second atmospheric data reference unit; the aircraft nose airspeed head respectively outputs an attack angle signal and a sideslip angle signal to a first atmospheric data reference unit and a second atmospheric data reference unit; and the output ends of the total temperature sensor and the field press binding device are respectively connected with the first atmospheric data reference unit and the second atmospheric data reference unit.
In order to better implement the present invention, the first static pressure atmospheric data module, the second static pressure atmospheric data module, the first total pressure atmospheric data module, and the second total pressure atmospheric data module respectively include a pressure sensor and an FPGA module, and are configured to convert an atmospheric pressure signal into a pressure digital signal, and transmit the pressure digital signal to the first atmospheric data reference unit and the second atmospheric data reference unit through an ARINC429 bus.
In order to better implement the method, the first static pressure atmospheric data module, the second static pressure atmospheric data module, the first total pressure atmospheric data module and the second total pressure atmospheric data module are respectively installed inside the aircraft nose and are close to the position of the nose airspeed head.
In order to better implement the utility model, the field-pressure binding device is respectively connected with the first atmospheric data reference unit and the second atmospheric data reference unit through field-pressure signal cables, and the field-pressure binding device, the first atmospheric data reference unit and the second atmospheric data reference unit are all installed in the aircraft equipment cabin.
In order to better implement the utility model, the first atmospheric data reference unit and the second atmospheric data reference unit are further used for resolving the air pressure altitude, the rising speed, the corrected airspeed, the vacuum speed, the mach number, the attack angle, the sideslip angle, the atmospheric static temperature and the large air density ratio according to the received aircraft nose airspeed head pipe attack angle signal, sideslip angle signal, total pressure digital signal, static pressure digital signal, total temperature resistance signal and field pressure signal and according to the navigation mark standard.
In order to better implement the utility model, the nose airspeed head is further mounted at the most front end outside the aircraft nose.
The utility model has the beneficial effects that:
(1) the aircraft nose airspeed head is arranged at the foremost end outside the aircraft nose, so that the total pressure, static pressure, attack angle feeling and sideslip angle feeling are slightly influenced by the position of the aircraft body, and the aircraft nose airspeed head has the characteristics of excellent pneumatic performance and simple correction of source position errors;
(2) on the premise of not increasing the weight, the atmospheric data module is realized by adopting the pressure sensor and the FPGA, so that electronic components are reduced, and the system cost is reduced; the air data module is arranged in the aircraft nose and is close to the position of the aircraft nose airspeed head, so that the air path hysteresis effect is small, and the air path dynamic response is fast;
(3) the novel dual-redundancy atmospheric data system disclosed by the utility model passes a large number of flight tests and is high in practicability; the utility model constructs an independent dual-redundancy atmosphere data system by using fewer line-level replaceable units, realizes the complete functions of the atmosphere data system, and ensures the requirements of high reliability and high safety of the atmosphere data system.
Drawings
Fig. 1 is a schematic block diagram of the present invention.
In the figure: 1, a nose airspeed head; 2, static pressure air pressure pipeline; 3, a first three-way gas path switching unit; 6, a first static pressure atmospheric data module; 7, a second static pressure atmospheric data module; 12, a total temperature sensor; 15, pressing and binding the device in the field; 18, a first atmospheric data reference unit; 19, a second atmospheric data reference unit; 20, a total pressure gas circuit pipeline; 21, a second three-way gas path switching unit; 24, a first total pressure atmospheric data module; and 25, a second total pressure atmosphere data module.
Detailed Description
Example 1:
a novel dual-redundancy atmospheric data system is shown in figure 1 and comprises an aircraft nose airspeed head 1, a field pressure binder 15 and a total temperature sensor 12, wherein the aircraft nose airspeed head 1 is respectively connected with a first three-way air path switching unit 3 and a second three-way air path switching unit 21 through a static pressure air path pipeline and a total pressure air path pipeline 20, the first three-way air path switching unit 3 is respectively connected with a first static pressure atmospheric data module 6 and a second static pressure atmospheric data module 7, and the second three-way air path switching unit 21 is respectively connected with a first total pressure atmospheric data module 24 and a second total pressure atmospheric data module 25; the first static pressure atmospheric data module 6 and the first total pressure atmospheric data module 24 respectively output static pressure digital signals and total pressure digital signals to be connected with the first atmospheric data reference unit 18, and the second static pressure atmospheric data module 7 and the second total pressure atmospheric data module 25 respectively output static pressure digital signals and total pressure digital signals to be connected with the second atmospheric data reference unit 19; the aircraft nose airspeed head 1 respectively outputs an attack angle signal and a sideslip angle signal to a first atmospheric data reference unit 18 and a second atmospheric data reference unit 19; the output ends of the total temperature sensor 12 and the field press binding device 15 are respectively connected with a first atmospheric data reference unit 18 and a second atmospheric data reference unit 19.
Further, the nose airspeed head 1 is arranged at the most front end outside the aircraft nose. The aircraft nose airspeed head 1 is adopted, the aircraft nose airspeed head 1 is arranged at the foremost end outside the aircraft nose, the influence of the total pressure, the static pressure, the attack angle feeling and the sideslip angle feeling on the position of the aircraft body is small, and the aircraft nose airspeed head has the characteristics of excellent pneumatic performance and simple correction of source position errors.
The novel dual-redundancy atmospheric data system disclosed by the utility model passes a large number of flight tests and is high in practicability; the utility model constructs an independent dual-redundancy atmosphere data system by using fewer line-level replaceable units, realizes the complete functions of the atmosphere data system, and ensures the requirements of high reliability and high safety of the atmosphere data system.
Example 2:
the embodiment is optimized on the basis of embodiment 1, and the first static pressure atmospheric data module 6, the second static pressure atmospheric data module 7, the first total pressure atmospheric data module 24, and the second total pressure atmospheric data module 25 respectively include a pressure sensor and an FPGA module, and are configured to convert an atmospheric pressure signal into a pressure digital signal, and transmit the pressure digital signal to the first atmospheric data reference unit 18 and the second atmospheric data reference unit 19 through an ARINC429 bus.
Further, the first static pressure atmospheric data module 6, the second static pressure atmospheric data module 7, the first total pressure atmospheric data module 24 and the second total pressure atmospheric data module 25 are respectively installed inside the aircraft nose and are close to the position of the nose airspeed head 1.
On the premise of not increasing the weight, the atmospheric data module is realized by adopting the pressure sensor and the FPGA, so that electronic components are reduced, and the system cost is reduced; the atmospheric data module is installed inside the aircraft nose, is close to the position of aircraft nose airspeed head 1, and the gas circuit hysteresis effect is little, has the corresponding fast advantage of gas circuit developments.
Other parts of this embodiment are the same as embodiment 1, and thus are not described again.
Example 3:
the present embodiment is optimized based on embodiment 1 or 2, the field-pressure binding device 15 is connected to the first atmospheric data reference unit 18 and the second atmospheric data reference unit 19 through field-pressure signal cables, and the field-pressure binding device 15, the first atmospheric data reference unit 18, and the second atmospheric data reference unit 19 are all installed in the aircraft equipment cabin.
Further, the first atmospheric data reference unit 18 and the second atmospheric data reference unit 19 are configured to calculate an air pressure altitude, a rising speed, a corrected airspeed, a vacuum speed, a mach number, an attack angle, a sideslip angle, an atmospheric static temperature, and an atmospheric density ratio according to the received aircraft nose pitot tube 1 attack angle signal, a sideslip angle signal, a total pressure digital signal, a static pressure digital signal, a total temperature resistance signal, and a field pressure signal, and according to a navigation mark standard.
The rest of this embodiment is the same as embodiment 1 or 2, and therefore, the description thereof is omitted.
Example 4:
a novel dual-redundancy atmospheric data system is shown in figure 1 and comprises an aircraft nose airspeed head 1, a three-way air path switching unit, an atmospheric data module, a total temperature sensor 12, a field pressure setter and an atmospheric data reference unit.
The aircraft nose airspeed head 1 has the functions of 1-way total pressure sensing, 1-way static pressure, 2-way attack angle output, 2-way side slip angle output and deicing prevention, and is arranged at the foremost end outside the aircraft nose.
The three-way air path switching unit is provided with 3 air path pipe connecting nozzles, and can realize the conduction of 3 air paths.
The atmospheric data module is realized by adopting a pressure sensor and an FPGA (field programmable gate array), converts an air pressure signal into a pressure digital signal, transmits the pressure digital signal to an atmospheric data reference unit through an ARINC429 bus, and is installed inside an aircraft nose at a position close to a nose airspeed head 1.
The atmospheric data reference unit has the function of resolving atmospheric parameters such as atmospheric altitude, rising speed, corrected airspeed, vacuum speed, Mach number, attack angle, sideslip angle, atmospheric static temperature, large air density ratio and the like according to the standard of a navigation mark according to received attack angle signals and sideslip angle signals of a nose airspeed head 1, total pressure digital signals resolved by an atmospheric data module, static pressure digital signals resolved by an atmospheric data module, total temperature resistance signals of a total temperature sensor 12 and field pressure signals of a field pressure binding device 15.
Further, as shown in fig. 1, the novel dual-redundancy atmospheric data system specifically comprises 1 aircraft nose airspeed head 1, 2 three-way gas path switching units, 4 atmospheric data modules, 1 total temperature sensor 12, 1 field pressure setter, and 2 atmospheric data reference units, and forms an independent dual-redundancy atmospheric data system according to a specific implementation manner.
Further, the total temperature sensor 12 of the present invention has a function of converting the total atmospheric temperature into 2 total temperature resistance signals.
Further, the field pressure setter has the function of 2-channel field pressure binding.
The novel dual-redundancy atmospheric data system disclosed by the utility model passes a large number of flight tests and is high in practicability; the utility model constructs an independent dual-redundancy atmosphere data system by using fewer line-level replaceable units, realizes the complete functions of the atmosphere data system, and ensures the requirements of high reliability and high safety of the atmosphere data system.
Example 5:
a novel dual-redundancy atmospheric data system is shown in figure 1, wherein a nose airspeed head 1 is arranged at the foremost end outside an aircraft nose; the aircraft nose airspeed head 1 is connected with a first three-way air path switching unit 3 through a static pressure air pressure pipeline 2 and is connected with a second three-way air path switching unit 21 through a total pressure air path pipeline 20; the aircraft nose airspeed head 1 is connected with the first atmospheric data reference unit 18 through an attack angle signal cable, is connected with the first atmospheric data reference unit 18 through a sideslip angle signal cable, is connected with the second atmospheric data reference unit 19 through an attack angle signal cable, and is connected with the second atmospheric data reference unit 19 through a sideslip angle signal cable.
The first three-way air path switching unit 3, the second three-way air path switching unit 21, the first static pressure atmospheric data module 6, the second static pressure atmospheric data module 7, the first total pressure atmospheric data module 24 and the second total pressure atmospheric data module 25 are arranged inside an aircraft nose and are close to the position of the aircraft nose airspeed head 1.
The first three-way gas path switching unit 3 is connected with a first static pressure atmosphere data module 6 through a gas pressure pipeline and is connected with a second static pressure atmosphere data module 7 through a gas pressure pipeline; the second three-way air path switching unit 21 is connected with the first total pressure atmospheric data module 24 through an air pressure pipeline and connected with the second total pressure atmospheric data module 25 through an air pressure pipeline.
The first static pressure air data module 6 is connected with a first air data reference unit 18 through a static pressure digital signal cable; the second static pressure atmospheric data module 7 is connected with a second atmospheric data reference unit 19 through a static pressure digital signal cable; the first total pressure atmosphere data module 24 is connected with the first atmosphere data reference unit 18 through a total pressure digital signal cable; the second total pressure atmosphere data module 25 is connected to the second atmosphere data reference unit 19 through a total pressure digital signal cable.
The total temperature sensor 12 is installed on the side surface of the aircraft nose, and is connected with a first atmospheric data reference unit 18 through a total temperature resistance signal cable, and is connected with a second atmospheric data reference unit 19 through a total temperature resistance signal cable.
The field press binding device 15, the first atmospheric data reference unit 18 and the second atmospheric data reference unit 19 are installed in an aircraft equipment cabin. The field binding device 15 is connected to a first atmospheric data reference unit 18 through a field pressure signal cable, and is connected to a second atmospheric data reference unit 19 through a field pressure signal cable.
The first atmospheric data reference unit 18 sends the calculated atmospheric parameters to other systems of the airplane through a cable; the second atmospheric data reference unit 19 sends the calculated atmospheric parameters to other systems of the aircraft via a cable.
The novel dual-redundancy atmospheric data system disclosed by the utility model passes a large number of flight tests and is high in practicability; the utility model constructs an independent dual-redundancy atmosphere data system by using fewer line-level replaceable units, realizes the complete functions of the atmosphere data system, and ensures the requirements of high reliability and high safety of the atmosphere data system.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way, and all simple modifications and equivalent variations of the above embodiments according to the technical spirit of the present invention are included in the scope of the present invention.
Claims (5)
1. A novel dual-redundancy atmospheric data system is characterized by comprising an aircraft nose airspeed head (1), a field pressure binding device (15) and a total temperature sensor (12), wherein the aircraft nose airspeed head (1) is respectively connected with a first three-way gas path switching unit (3) and a second three-way gas path switching unit (21) through a static pressure gas path pipeline (2) and a total pressure gas path pipeline (20), the first three-way gas path switching unit (3) is respectively connected with a first static pressure atmospheric data module (6) and a second static pressure atmospheric data module (7), and the second three-way gas path switching unit (21) is respectively connected with a first total pressure atmospheric data module (24) and a second total pressure atmospheric data module (25); the first static pressure atmospheric data module (6) and the first total pressure atmospheric data module (24) respectively output static pressure digital signals and total pressure digital signals to be connected with a first atmospheric data reference unit (18), and the second static pressure atmospheric data module (7) and the second total pressure atmospheric data module (25) respectively output static pressure digital signals and total pressure digital signals to be connected with a second atmospheric data reference unit (19); the aircraft nose airspeed head (1) respectively outputs an attack angle signal and a sideslip angle signal to a first atmospheric data reference unit (18) and a second atmospheric data reference unit (19); the output ends of the total temperature sensor (12) and the field press binding device (15) are respectively connected with a first atmospheric data reference unit (18) and a second atmospheric data reference unit (19);
the first atmospheric data reference unit (18) and the second atmospheric data reference unit (19) are used for resolving an air pressure height, a rising speed, a corrected airspeed, a vacuum speed, a Mach number, an attack angle, a sideslip angle, an atmospheric static temperature and an atmospheric density ratio according to a received attack angle signal, a sideslip angle signal, a total pressure digital signal, a static pressure digital signal, a total temperature resistance signal and a field pressure signal of the nose airspeed head (1) and a navigation mark standard.
2. The novel dual-redundancy atmosphere data system according to claim 1, wherein the first static pressure atmosphere data module (6), the second static pressure atmosphere data module (7), the first total pressure atmosphere data module (24) and the second total pressure atmosphere data module (25) respectively comprise a pressure sensor and an FPGA module, and are used for converting an air pressure signal into a pressure digital signal and transmitting the pressure digital signal to the first atmosphere data reference unit (18) and the second atmosphere data reference unit (19) through an ARINC429 bus.
3. The novel dual-redundancy atmospheric data system of claim 2, wherein the first static pressure atmospheric data module (6), the second static pressure atmospheric data module (7), the first total pressure atmospheric data module (24) and the second total pressure atmospheric data module (25) are respectively installed inside an aircraft nose and are close to the position of the airspeed head (1).
4. The novel dual-redundancy atmospheric data system as claimed in claim 1, wherein the field-pressure binder (15) is connected with the first atmospheric data reference unit (18) and the second atmospheric data reference unit (19) through field-pressure signal cables, and the field-pressure binder (15), the first atmospheric data reference unit (18) and the second atmospheric data reference unit (19) are installed in an aircraft equipment cabin.
5. The novel dual-redundancy atmospheric data system of claim 1, wherein the nose airspeed head (1) is mounted at the outer most front end of the aircraft nose.
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| CN115876243A (en) * | 2023-03-08 | 2023-03-31 | 航宇伟创科技(北京)有限公司 | Aircraft atmospheric data system check out test set |
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