JP2003165498A - Navigation support system, aircraft and navigation support method - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To secure the sufficient safety in relation to the wake vortex, and to improve the transportation efficiency of an aircraft. <P>SOLUTION: A memory unit 4 stores a weight data base 4a of kinds of aircraft and weight thereof related to each other. Area of a range to be influenced by the wake vortex is previously computed on the basis of the weight of the aircraft, and a range data base 4b thereof is stored in the memory unit 4. An information obtaining unit 5 obtains kinds of peripheral equipment, and weight of the peripheral equipment is specified on the basis of the weight data base 4a. A range of the peripheral equipment to be influenced by the wake vortex is specified on the basis of the range data base 4b. The specified wake vortex range is displayed in a display unit 2 with a peripheral equipment symbol in a direction corresponding to the speed of the peripheral equipment obtained by the information obtaining unit 5. <P>COPYRIGHT: (C)2003,JPO

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a navigation support device used by being mounted on an aircraft, an aircraft equipped with the navigation support device, and a navigation support method.

[0002]

2. Description of the Related Art With the recent increase in the size of aircraft, the danger of wake vortex is drawing attention. Wake vortex, also called waker burence, or wake turbulence, is a vortex of air flow generated from the wing tip of an aircraft toward the rear. The strength of the vortex is expressed by the following equation (1).

[Equation 1] Here, the airframe form factor and the main wing span are parameters defined as airframe design data. There was also an accident in which a small aircraft crashed due to being caught in a wake vortex generated by a large aircraft.

As a measure for reducing the wake vortex, there is a winglet provided at the tip of the main wing. However, even winglets cannot extinguish the wake vortex, which is not a fundamental solution. Therefore, at present, aircraft operations are being carried out to avoid wake vortex by air traffic control. For example, for international passenger aircraft, the flight interval of the aircraft (hereinafter referred to as separation) is a certain time or more (for example, 2
There is a rule to secure it (more than a minute). Controllers constantly monitor passenger aircraft for compliance with this rule, and make sure that subsequent aircraft are not caught in the Wake Vortex.

By the way, a super-large-sized aircraft having a scale larger than that of the large-sized aircraft at present is under development. In such an ultra-large machine, countermeasures against wake vortex are one of the main issues, but at present, there is only countermeasure to further lengthen the separation. Prolonged separation leads to a reduction in aircraft transportation efficiency. Therefore, it is feared that the economical efficiency of air transportation may be offset by the reduction in transportation efficiency even if the loading capacity increases due to the super-large-sized aircraft.

In addition, a new CNS / ATM (Communication Navigation Surveilla), which is planned to be fully operated in the future,
nce / Air Traffic Management), it is considered to reduce the monitoring by air traffic control. The pilot
ADS-B (Automatic Dependent Surveillance-Bro
Adcast) system will fly while monitoring the aircraft around it. In such an environment, securing of safe separation is mainly entrusted to the pilot, and there is a demand for development of a device that supports this.

[0006]

As described above, in conventional air transportation, it is required to allow sufficient separation as a countermeasure against the wake vortex, which is a factor that reduces the transportation efficiency. Has become. In addition, the new CNS / planned for full operation in the future
ATMs need to provide wake vortex countermeasures that are less dependent on air traffic control.

The present invention has been made under the above circumstances.
It is an object of the present invention to provide a navigation support device, an aircraft and a navigation support method that can secure sufficient safety against wake vortex and improve the transportation efficiency of the aircraft.

[0008]

In order to achieve the above object, the present invention relates to a navigation support device mounted on an aircraft and used, and a wake generated by the target aircraft in an attribute provided for each aircraft. Storage means for storing a wake vortex database in which information indicating areas affected by vortexes is associated and stored, attribute acquisition means for acquiring attributes of aircraft existing in a predetermined airspace, and acquisition by this attribute acquisition means Based on the attribute of the aircraft and the wake vortex database, the calculation means for obtaining the region affected by the wake vortex of the aircraft, the relative position between the aircraft equipped with its own device and the region obtained by the calculation means. And a display means for visually displaying the physical positional relationship.

By taking such means, for example, the aircraft number, flight number, of the aircraft existing in the predetermined airspace,
Attributes such as weight, speed, or traveling direction are acquired by the attribute acquisition unit. Based on this attribute and the wake vortex database, the calculation unit can obtain the area affected by the wake vortex of the aircraft. The relative positional relationship between this area and, for example, the player's own machine is visually displayed by the display means as, for example, a symbol mark.

Therefore, according to the present invention, the invisible wake vortex is visualized,
It is possible to inform the pilot more directly of the range of influence of the wake vortex. This will inform the pilot of the danger of wake vortex and improve flight safety.

Further, since the range of influence of the wake vortex can be directly recognized, it is not necessary to secure an unnecessary separation. Therefore, the efficiency of air transportation can be improved, and the economic efficiency of air transportation can be improved.

Further, the present invention further provides an informing means for issuing an alarm such as a buzzer sound when the distance between the aircraft equipped with the own apparatus and the area obtained by the arithmetic means becomes smaller than a specified value. It is characterized by including. By doing so, it is possible to further draw the attention of the pilot and further improve flight safety.

[0013]

BEST MODE FOR CARRYING OUT THE INVENTION Hereinafter, embodiments of the present invention will be described in detail with reference to the drawings. FIG. 1 is a diagram showing an example of an aircraft equipped with a navigation support device according to an embodiment of the present invention. This aircraft is equipped with an antenna 51 for an ATC transponder. Reference numeral 6 indicates a winglet, which is a winglet which is erected on the main wing tip as shown in FIG.

FIG. 2 is a diagram showing an example of the appearance of the cockpit of the aircraft shown in FIG. In the cockpit, a display unit 2 for visually displaying various information and an FMC (Flight M
anagement Computer) and. The FMC is provided with an operation console (without reference numeral) that receives information input by the pilot, an arithmetic unit that processes various kinds of information, and the like.

FIG. 3 is a functional block diagram showing the configuration of the navigation support device according to this embodiment. This device is used by being mounted on an aircraft and includes a calculation unit 1, a display unit 2, a notification unit 3, a storage unit 4, and an information acquisition unit 5. Of these, the calculation unit 1 and the storage unit 4 may be incorporated in the FMC, for example.

The arithmetic unit 1 is, for example, a CPU (Central Process).
It is realized as a sing unit) and controls the device as a whole. The display unit 2 is realized as a liquid crystal display or the like and visually provides various information to the pilot of the aircraft. The notification unit 3 includes an alarm lamp 31 and a speaker 32, and issues an alarm to call the pilot's attention.

The storage unit 4 stores software for realizing the operation of the CPU and various databases. In the present embodiment, the weight database 4a is stored in the storage unit 4.
And area database 4b are stored. Information acquisition unit 5
Equipped with an antenna 51, a Mode S transponder,
Alternatively, it is realized as an ADS-B receiver or the like. The information acquisition unit 5 determines the position, altitude, model, or speed (progress) of an aircraft (hereinafter, referred to as a peripheral aircraft) existing around the aircraft (more specifically, within an airspace of a predetermined size including the aircraft). Information (including direction) is also acquired. Hereinafter, these pieces of information are referred to as aircraft (peripheral aircraft) attributes.

FIG. 4 is a schematic diagram showing the contents recorded in the area database 4b. The area database 4b is a database in which the aircraft model is associated with the area affected by the wake vortex generated from the aircraft. Since the strength of the wake vortex vortex is proportional to the weight and the velocity, the size of the affected area also depends on the weight and the velocity. However, the weight is almost uniquely determined by the model. Further, the wake vortex is mainly a problem immediately after take-off or just before landing when the distance between aircraft is narrowed, and the speed in such a flight phase is almost uniquely determined by the model. Therefore, in the present embodiment, the size of the region affected by the wake vortex is determined based on the aircraft model, and the database is stored in the storage unit 4 in advance.

FIG. 5 is a flow chart showing a processing procedure in the navigation support device having the configuration shown in FIG. Figure 5
In step S1 of step 1, the information acquisition unit 5 acquires the attributes such as the position, altitude, model, or speed (including the traveling direction) of the peripheral aircraft with respect to the aircraft equipped with the navigation support device (hereinafter, referred to as own aircraft). It The number of peripheral devices is not limited to one, and there may be a plurality of peripheral devices.

Area database 4b from the acquired model
With reference to step S2, the area affected by the wake vortex of each peripheral is specified in step S2. In the next step S3, the symbol indicating the peripheral device is displayed on the display unit 2 together with the symbol indicating the own device. FIG. 6 shows a display state on the display unit 2. For example, existing ACAS
Similar to the display example in (Aircraft Collision Avoidance System), the own machine symbol is displayed in the center of the screen, and the peripheral machine symbol is displayed at the coordinates corresponding to the position of the peripheral machine in the screen. Peripheral aircraft symbol is
The shape may be changed for distinction. Further, information such as the altitude and model of the corresponding peripheral device may be displayed beside the peripheral device symbol.

In the next step S4 (FIG. 5), the area affected by the wake vortex of each peripheral device specified in step S2 is displayed over each peripheral device symbol. FIG. 7 shows a display state on the display unit 2 at this stage. In this way, the range affected by the wake vortex is displayed on the display unit 2 by overlapping the peripheral device symbol.
Is displayed in. The wake vortex spreads behind the aircraft. Therefore, the speed (including the traveling direction) of the aircraft (peripheral aircraft) acquired in step S1 is referred to so that the symbol indicating the wake vortex is always displayed behind the peripheral aircraft. According to Fig. 7, the peripheral aircraft at the bottom right of the screen flies from the top to the bottom of the figure (that is, in the opposite direction to the aircraft), and the other peripheral aircraft flies from the bottom to the top of the figure (that is, the aircraft chases). I know what to do. Of course, the wake vortex picked up by the peripheral aircraft flying in the diagonal direction is also displayed in the diagonal direction on the display unit 2.

In the next step S5 (FIG. 5), the three-dimensional relative distance between the area affected by the wake vortex of each peripheral machine specified in step 3 and the own machine position is calculated. The calculated relative distance is compared with a predetermined specified value. If the relative distance is greater than or equal to the specified value in step S5, the processing procedure returns to step S1. On the other hand, if the relative distance is smaller than the specified value, the processing procedure proceeds to step S6, and the alarm unit 3 issues an alarm.

FIG. 8 is a schematic diagram showing a situation when an alarm is issued in this embodiment. On the screen of the display unit 2, when a circle centered on the own position symbol and having a radius equal to the first specified value (referred to as a first circle) does not overlap the area affected by the wake vortex,
No warning is given as none. From this state, when the own aircraft and the peripheral aircraft approach each other and the first circle and the wake vortex region overlap, an alarm is issued. In this case, "Cautio", which has a relatively low risk,
The message “n” is issued. This message may be issued in the form of a voice message by the speaker 32 via the notification unit 3, or characters or the like may be displayed on the screen of the display unit 2.

As shown in FIG. 9, a circle (referred to as a second circle) having a second prescribed value as a radius centered on the own machine position symbol and the wake vortex as shown in FIG. If it overlaps with the area, "Al
ert "message is generated.
For example, blinking the alarm lamp 31 or changing the display color of the display unit 2
The form will be used to notify the pilot of the impending danger.

As described above, in this embodiment, the weight database 4a in which the aircraft model name is associated with the weight is stored in the storage unit 4. In addition, the size of the area affected by the wake vortex is calculated in advance based on the aircraft weight,
The area database 4b, which is a database of this, is stored in the storage unit 4. Then, the information acquisition unit 5 acquires the model name of the peripheral machine, and specifies the weight of the peripheral machine from the weight database 4a. Based on this, the area affected by the wake vortex of the peripheral device is specified from the area database 4b. The specified wake vortex area is displayed on the display unit 2 together with the peripheral device symbol in the direction corresponding to the speed of the peripheral device acquired by the information acquisition unit 5.

Since this is done, the airspace in danger is visualized by the wake vortex, and the display unit 2
Is displayed in. This allows the pilot to more directly recognize the wake vortex, which is otherwise invisible. Therefore, it can contribute to the safe operation of the aircraft.

Furthermore, the discretion of the pilot makes it possible to minimize the separation. This makes it possible to streamline air transportation while maintaining safety. Therefore, it becomes possible to improve the economical efficiency of air transportation.

Further, the area affected by the wake vortex is not calculated during the flight of the aircraft itself, but is obtained by reading it from a table (database) prepared in advance. This can increase the processing speed and further contribute to safe operation. Of course, if the capacity of the processor is sufficient, the wake vortex region may be calculated by a mathematical expression from the weight and speed of the aircraft.

Further, in the present embodiment, an alarm is issued when the position of the self-apparatus and the wake vortex area approach each other. In the conventional ACAS, the alarm is issued only when the own aircraft approaches the peripheral aircraft. On the other hand, in the present embodiment, an alarm is issued even when the own aircraft approaches the wake vortex area. This allows
It can further contribute to flight safety.

The present invention is not limited to the above embodiment. For example, in the present embodiment, the gross weight (Gross) considering the fuel, the number of passengers, the cargo loading amount, and the like from the peripheral model by communication means such as a mode S transponder.
s Weight) and moving airspeed (True Air Speed), and the like, and the process of identifying the wake vortex region from these information is performed. Instead of this, a database in which the model and the wake vortex region are associated with each other is prepared, and by using this database, the wake vortex region may be directly obtained from the model. In addition to the model, other attributes such as flight number and shape can be used. In short, the wake vortex area may be associated with the attributes of the aircraft.

Further, it may be displayed such that the spread of the wake vortex region in the horizontal direction changes depending on the altitude. Therefore, the width of the wake vortex symbol displayed on the display unit 2 may be changed according to the altitude difference between the own device and the peripheral device. This can be easily realized by the predetermined arithmetic processing in the arithmetic unit 1. Of course, it is possible to take into account the vertical change of the wake vortex region when issuing the alarm.

Further, the size of the wake vortex region acquired from the database may be adjusted in consideration of the total weight of the surrounding aircraft and the moving airspeed.

Further, the current communication between aircrafts is realized by a method of "replying a response to a question". On the other hand, in the next-generation navigation system, it is attempted to realize inter-aircraft communication by a method in which an aircraft in flight transmits various information in a so-called broadcast manner and other aircraft receive the information. There is. In such a system, the area data covered by the wake vortex of the aircraft may be included in various information transmitted by the aircraft. Even with this,
It becomes possible to recognize the wake vortex area of the peripheral aircraft in the aircraft in flight. In addition, various modifications can be made without departing from the scope of the present invention.

[0034]

As described in detail above, according to the present invention, a navigation support device, an aircraft, and a navigation support method that can secure sufficient safety against wake vortex and improve the transportation efficiency of an aircraft are provided. be able to.

[Brief description of drawings]

FIG. 1 is a diagram showing an example of an aircraft equipped with a navigation support device according to an embodiment of the present invention.

FIG. 2 is a diagram showing an example of an external appearance of a cockpit of the aircraft shown in FIG.

FIG. 3 is a functional block diagram showing a configuration of a navigation support device according to an embodiment of the present invention.

FIG. 4 is a schematic diagram showing contents recorded in a region database 4b.

5 is a flowchart showing a processing procedure in the navigation support device having the configuration shown in FIG.

FIG. 6 is a diagram showing a display state on the display unit 2.

FIG. 7 is a diagram showing a display state on the display unit 2.

FIG. 8 is a schematic diagram showing a situation when an alarm is issued in the embodiment of the present invention.

FIG. 9 is a schematic diagram showing a situation when an alarm is issued in the embodiment of the present invention.

[Explanation of symbols]

1 ... Calculator 2 ... Display 3 ... Notification section 31 ... Alarm lamp 32 ... speaker 4 ... storage unit 4b ... Area database 5 ... Information acquisition unit 51 ... antenna 6 ... Winglet

Claims (13)

[Claims] 1. In a navigation support device used on board an aircraft, a database is created by associating the attributes provided for each aircraft with the information indicating the area affected by the wake vortex generated by the target aircraft. Based on the wake vortex database, a storage means for storing the wake vortex database, an attribute acquisition means for acquiring the attribute of an aircraft existing in a predetermined airspace, an attribute of the aircraft acquired by the attribute acquisition means, and the wake vortex database. A calculation means for obtaining an area affected by the wake vortex of the aircraft, and a display means for visually displaying a relative positional relationship between the aircraft equipped with the own device and the area obtained by the calculation means. A navigation support device characterized by: 2. The wake vortex database includes an area database in which information indicating an aircraft model is associated with information indicating an area affected by the wake vortex, and the computing means includes the attribute acquisition means. The aircraft model corresponding to the attribute of the aircraft acquired in 1. is searched from the area database, and the information indicating the area affected by the wake vortex of the aircraft is acquired from the area database. The navigation support device according to 1. 3. The wake vortex database includes a model-to-region database in which information indicating a region affected by the wake vortex is associated with each aircraft model to form a database, and the attribute acquisition unit has a predetermined airspace. In order to obtain information indicating at least the model of the aircraft existing in the, the calculation means, the area affected by the wake vortex of the aircraft corresponding to the information indicating the model of the aircraft acquired by the attribute acquisition means The information indicating the information is acquired from the model-to-area database.
Navigation support device described in. 4. The calculation means changes the shape of the area displayed on the display means in accordance with an altitude difference between an aircraft equipped with its own device and an aircraft existing in the predetermined airspace. The navigation support device according to claim 1, wherein: 5. The system further comprises an alerting means for issuing an alert when the distance between the aircraft equipped with the own device and the area obtained by the computing means becomes smaller than a specified value. The navigation support device according to any one of claims 1 to 4. 6. The informing means changes the alarm level stepwise according to the distance between the aircraft equipped with its own device and the area obtained by the computing means. Navigation support device described in. 7. An aircraft comprising the navigation support device according to claim 1. 8. A navigation assisting method using a navigation assisting device mounted on an aircraft, comprising: a first step of acquiring attributes of an aircraft existing in a predetermined airspace; Based on the attributes of the aircraft acquired in the first step, and the wake vortex database that is a database in which the information indicating the area affected by the wake vortex generated by the target aircraft is associated with the attributes respectively provided, A second step of obtaining an area affected by the wake vortex of the aircraft, and a third step of visually displaying a relative positional relationship between the aircraft and the area obtained in the second step on a display unit. A navigation support method comprising: 9. The aircraft model corresponding to the attribute of the aircraft acquired in the first step from the area database in which the aircraft step information is associated with the aircraft model attribute information in the database in the second step. 9. The navigation support method according to claim 8, further comprising the step of retrieving information and acquiring the region affected by the wake vortex of the aircraft corresponding to the retrieved model information from the region database. 10. The first step is a step of acquiring at least model information of an aircraft existing in a predetermined airspace, and the second step shows a region affected by wake vortex for each aircraft model. From the model-to-area database in which information is associated and made into a database, the first
9. The navigation support method according to claim 8, further comprising the step of acquiring an area affected by the wake vortex of the aircraft corresponding to the aircraft model information obtained in the step. 11. The method further comprises a fourth step of changing the shape of the area displayed on the display unit according to the altitude difference between the aircraft and the aircraft existing in the predetermined airspace. The navigation support method according to claim 8. 12. The method according to claim 5, further comprising a fifth step of issuing an alarm when the distance between the player and the area obtained in the second step becomes smaller than a specified value. The navigation support method described in 8 or 11. 13. The method according to claim 12, further comprising a sixth step of gradually changing an alarm level according to a distance between the player's own aircraft and the area obtained in the second step. Navigation support method described in.