JP2003271707A - System and method for assisting airspace designing - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide an airspace designing assisting system which accurately and speedily can inspect an obstacle by a computer. <P>SOLUTION: The system is to inspect whether there is an obstacle to a no-obstacle surface which includes two or more planes having different gradients and is computed under a plurality of conditions based upon a reference inspection line as a border to be the reference for inspection regarding an obstacle in a protection airspace of the flight path of an airplane, is equipped with a no-obstacle surface calculation condition input means 101 which inputs the calculation conditions of the no-obstacle surface, an inspected object information input means 102 which inputs information showing one or more objects to be inspected, a dividing means 103 which divides the no-obstacle surface into a plurality of polygonal surfaces by the gradients based upon the reference inspection line, a judging means 104 which compares the altitude of the no-obstacle surface, calculated by using a plurality of calculation expressions determined by the divided polygonal surfaces, with the altitude of the object to be inspected to judge whether there is the obstacle, and an output means 105 which outputs the result of judgement of whether there is the obstacle. <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 an airspace design support system and method for supporting airspace design work in the field of aviation, and more particularly to designing a protected airspace corresponding to a return route used when an aircraft re-lands. The present invention relates to an airspace design support system and method suitable for use in supporting work.

[0002]

2. Description of the Related Art In addition to a normal takeoff or landing route, a flight route set when an aircraft flies includes a return route used for re-landing. The design of this return route is performed based on a predetermined design standard. When setting up a return route, it is necessary to secure a corresponding protected airspace (an area where it is obligatory to confirm that there are no obstacles on the route).

The return route may include a route for turning, and the protective airspace is composed of a complicatedly curved plane or curved surface. Then, it is necessary to confirm that there is no obstacle at each coordinate on the surface. This obstacle confirmation surface is calculated as a single surface or a combination of multiple surfaces with a certain gradient in the protected airspace, and it is an obstacle-free surface (a surface where no obstacles should protrude). )It is called. The calculation conditions for the obstacle-free surface are determined in several different forms according to the airspace design standard (airspace design method).

As described above, when installing a flight route (route) for an aircraft to fly, such as a return route, the protection airspace along the route is set and protected based on the airspace design standard adopted. It is necessary to verify whether or not the obstacle interferes with the obstacle-free surface having a predetermined slope in the airspace. The main design criteria are the Japanese method applied by civil aviation in Japan and the US method applied by the Defense Agency. In Japan's airspace design method, an obstacle-free surface is a flat surface with a certain slope, and therefore it is possible to verify obstacles with a single formula for the designed and drawn shape.
Therefore, based on the entered information, the route conditions and whether or not a line segment intersects with another line segment are determined to calculate the coordinates for shape / verification and the surface of the obstacle-free. ing.

[0005]

However, in the US airspace design method, the unobstructed surface, which is the reference for verification, is a three-dimensional and complex surface, and the changing conditions are complicated. When the determination is made by the same route setting condition as the case or the pattern matching by the intersection of the line segments, the number of patterns reaches several hundreds. In such a case, the amount of calculation becomes enormous and it is difficult to obtain the calculation result immediately when the condition is changed. Therefore, it cannot be said that the design support by the computer is always effective, and the altitude calculation of each coordinate on the plane is often performed manually. Therefore, automation of altitude calculation has been desired.

The present invention has been made in consideration of the above circumstances, and enables an obstacle to be accurately and promptly verified by a computer, and by promoting automation of verification of a protected airspace, An object is to provide an airspace design support system and method that can improve the work efficiency of a designer.

[0007]

In order to solve the above-mentioned problems, the invention according to claim 1 includes a criterion for verification concerning obstacles including two or more planes having different slopes in a protected airspace of a flight path of an aircraft. A system for verifying the presence / absence of an obstacle with respect to an obstacle-free surface which is calculated under a plurality of different conditions with a verification reference line as a boundary, and which inputs a calculation condition for the obstacle-free surface. Input means, second input means for inputting information indicating one or a plurality of verification objects, and division for dividing the obstacle-free surface into a plurality of polygonal surfaces for each gradient with reference to the verification reference line. Determining means for comparing the altitude of the obstacle-free surface calculated using a plurality of calculation formulas defined for each of the divided polygonal surfaces with the altitude of the verification object, and determining the presence or absence of an obstacle. And an output means for outputting the judgment result of presence or absence of an obstacle. And wherein the Rukoto. According to a second aspect of the present invention, each of the calculation formulas defined for each of the polygonal surfaces is such that the altitude of each point of the polygonal surface is defined by one or a plurality of continuous line segments or one on the outer periphery of each polygonal surface. It is characterized in that it is obtained by a multiplication / division operation in which the shortest distance obtained by using a point as a reference is multiplied by a gradient, and a predetermined addition / subtraction operation.

According to a third aspect of the present invention, in a protected airspace of a flight path of an aircraft, a plurality of planes having different slopes are included, and a plurality of different conditions are set at a boundary of a verification reference line which is a reference for verification of an obstacle. A method for verifying the presence or absence of an obstacle on a calculated obstacle-free surface using a computer, comprising a first step of inputting calculation conditions for the obstacle-free surface, and one or more verifications. The second step of inputting information indicating the object, and the altitude of the obstacle-free surface and the verification object for each polygonal surface obtained by dividing the obstacle-free surface into a plurality of gradients with the verification reference line as a boundary. And a third step of outputting the comparison result as a determination result of the presence or absence of an obstacle.

[0009]

BEST MODE FOR CARRYING OUT THE INVENTION Embodiments of the present invention will be described below with reference to the drawings. FIG. 1 is a block diagram showing the basic configuration of an embodiment of an airspace design support system according to the present invention. The airspace design support system according to the present embodiment includes a computer, an input device such as a keyboard and a mouse, an output device such as a display and a printer, and a computer peripheral device such as a communication device for a network,
It is composed of a program executed on a predetermined OS (operating system) in the computer. FIG. 1 shows the main functions of this embodiment realized by the program in blocks.

The main function realized by the airspace design support system shown in FIG. 1 is to include a verification reference line that includes two or more planes with different slopes in the protection airspace of the flight path of an aircraft and that serves as a reference for obstacle verification. It is a system for verifying the presence or absence of an obstacle on the surface of an obstacle (a surface on which the obstacle should not protrude) calculated under a plurality of different conditions (starting points) at the boundary. The airspace design support system of the present embodiment can support the design of flight routes during normal takeoff and landing and flight routes between airports by combining with other functions not shown in FIG. However, in the following, the function used to support the design of the protected airspace corresponding to the return route used when the aircraft re-lands will be described in detail.

The system shown in FIG. 1 has an obstacle-free surface calculation condition input means 101 and a verification certificate object information input means 10.
2, a dividing means 103, a judging means 104, and an output means 105. The obstacle-free surface calculation condition input means 101 has a function of inputting the calculation condition of the obstacle-free surface, and can be input interactively using a mouse or a keyboard, or registered input information can be input internally or externally. By reading from the recording medium, the obstacle-free surface calculation method, definition information including verification reference line and setting information for each gradient,
Input or update calculation conditions such as coordinate information indicating runways and return routes. Verification object information input means 10
Reference numeral 2 denotes information indicating the position and altitude of one or more verification objects to be verified, which is the obstacle-free surface calculation condition input means 1
This is a function for inputting similarly to 01.

Based on the calculation conditions for the obstacle-free surface input by the obstacle-free surface calculation condition input means 101, the dividing means 103 divides the obstacle-free surface into a plurality of gradients with respect to the verification reference line. It is a function to divide into rectangular surfaces. The determination means 104 obtains the altitude of the obstacle-free surface based on a calculation formula determined according to a plurality of calculation formula patterns predetermined for each polygonal surface divided by the dividing means 103,
This is a function of comparing the altitude of each verification object input by the verification certificate object information input means 102 and determining the presence or absence of an obstacle. The output means 105 then determines the determination means 10
It is a function of outputting the judgment result of the presence / absence of an obstacle by 4 on a display or printer.

Before describing the details of each means shown in FIG. 1, a method for calculating the altitude of an obstacle-free surface at any one point according to the regulations of the US airspace design system to which this embodiment is applied will be described. To do.

(1) First, the primary area and the secondary area of the obstacle-free surface will be described. In the US airspace design scheme, there are primary areas 11 and secondary areas 21, 22 as shown in FIG. FIG. 2 shows the return route 10
FIG. 3 is a plan view of the obstacle-free surface 1 and the runway 2 (or the final approach area 2 including the runway) as seen from above. The primary area 11 is in contact with the runway 2 and the slope of the obstacle-free surface is 4
The secondary sections 21, 22 consist of surfaces that rise at 0: 1, and the sloped surfaces that rise further by 15: 1 from the inwardly contacting primary section 11.

Next, with reference to FIGS. 3 and 4, a specific example of calculating the altitude of the obstacle-free surface at any one point in the setting example of the return route 10 with respect to the position of the runway 2 shown in FIG. To explain. In this example, the altitude of the obstacle-free surface 21 in the secondary area of the point B corresponding to the position of the obstacle 3 shown in the plan view of FIG. 3 is calculated.

As a prerequisite, the altitude of the primary section 11 at the point Y (the end point on the right side as viewed from the top of the runway 2 (or the end point corresponding to the turning start point of the final approach section 2)) is 300 FT (300 FT). Feet: about 91.44 meters), the shortest horizontal distance from the obstacle 3 to the line segment VW (line segment BP) = 1.1NM (nautical mile) = 668
4FT, shortest horizontal distance from point P to point Y = 18NM =
The conditions of 109381 FT, primary zone 11 gradient 40: 1, secondary zone 21, 22 gradient 15: 1 are used.

The primary area 11 is set to have an outer shape having a predetermined spread so as to surround the backward path 10. That is, for example, the outline on the side in contact with the secondary area 21 is a point from the point X (the left end point when viewed from above the tip of the runway 2 (or the end point corresponding to the turning start point of the final approach area 2)). U (primary area 11 and secondary area 2
A curve connecting the contact points 1) and points U and W (point U)
A straight line connecting the end point of the line segment starting from and the points W and V
And a straight line connecting (the end point of the line segment starting from the end point of the point W and one end point of the surface of the obstacle).
Here, the line segment WV is a straight line parallel to the straight line portion of the backward path 10.

In the above case, the line segment YP and the line segment P are shown in FIG.
As shown in the schematic side view (FIG. 4) viewed from the direction perpendicular to B, the altitude of the obstacle-free surface at point B = (6684 ÷ 15)
+ (109381 ÷ 40) + 300 = 3480FT. Therefore, if the obstacle 5 is lower than 3480FT, it is determined that the obstacle-free surface 1 is not touched.

(2) Next, the starting point at the time of calculation will be described with reference to FIGS. 5 to 10, which are plan views similar to FIG. When calculating the height of the obstacle-free surface, the slope is 40: 1 for the primary area and 15: for the secondary area, as described above.
Although it is 1, the starting point depends on the shape part as follows. It is assumed that the altitudes at the points X, Y, and Z (points 1 NM away from the point Y on the outline of the runway 2 (or the final approach area 2)) are the same.
Further, the straight line 31 is a straight line perpendicular to the line segment XY, and the straight line 3
2 It is a straight line that is orthogonal to it and serves as the vertical axis and the horizontal axis of the coordinate system.

For example, as shown in FIG. 5, the base point for calculating the altitude in the primary area 11 surrounded by the line segment XY and the straight line 31 is the line segment XY. Then, the shortest distance to the line segment XY (the line segment X
The length of the perpendicular to Y) multiplied by the slope (40: 1) is the height of the unobstructed surface.

Further, as shown in FIG. 6, the base point for calculating the altitude in the primary area 11 surrounded by the straight line 31 and the straight line 32 is the point Y. Then, the gradient (40:
The product of 1) is the altitude of the obstacle-free surface.

Further, as shown in FIG. 7, the base point for calculating the altitude in the primary area 11 surrounded by the line segment YZ and the straight line 32 is the line segment YZ. Then, the shortest distance to the line segment YZ (the line segment Y
The length of the perpendicular to Z) multiplied by the slope (40: 1) is the height of the unobstructed surface.

Further, as shown in FIG. 8, the base point for calculating the altitude in the range on the point U side of the secondary area 21 enclosed by the perpendicular drawn from the line segment UW is the line segment UW. Then, a gradient (15: to the shortest distance to the line segment UW (the length of the perpendicular to the line segment UW)).
The product of 1) and the altitude in the primary area 11 of the position of the foot of the perpendicular in the line segment UW are added to obtain the altitude of the obstacle-free surface.

Further, as shown in FIG. 9, the point W is the base point for calculating the altitude in the range surrounded by the perpendicular drawn from the line segment UW and the perpendicular drawn from the line segment WV. Then, the sum of the shortest distance to the point W multiplied by the gradient (15: 1) and the height in the primary area 11 of the point W is the height of the obstacle-free surface.

Then, as shown in FIG. 10, the base point for calculating the altitude in the range on the point V side of the secondary area 21 surrounded by the perpendicular drawn from the line segment WV is the line segment WV. And the line segment WV
To the shortest distance (length of the perpendicular to the line segment WV) (1
5: 1) and the altitude in the primary area 11 of the position of the foot of the perpendicular in the line segment WV are added to obtain the altitude of the obstacle-free surface.

Even in the same secondary area, if the parts of the primary area that are in contact are different, the calculation starting points of the primary areas are different. That is, as shown in FIG. 11, the obstacle C,
Both D belong to the secondary area described in FIG. 8, but the obstacle C is the range described in FIG.
Since the obstacle D is in contact with the range described in FIG. 6, the calculation starting points for the primary areas are different.

(3) Next, referring to FIGS. 12 to 18,
The verification reference line and the method of altitude calculation using it will be explained. As shown in FIG. 12, the verification reference line is the runway 2 from the point 1 NM before the turning start point S toward the turning inside.
A virtual line segment 42 drawn perpendicular to and the final approach area 2
(Or runway 2) is a line segment composed of a part 41. The verification reference line is used as a reference when the unobstructed surface 10 is set to include a point that has returned by 1 NM or more from the turning start point S in the flight direction. The starting point at the time of calculating the altitude of the obstacle-free surface 10 changes with the verification reference lines 41 and 42 as a boundary.

In the example shown in FIG. 13, the shaded portion of the obstacle-free surface 10 is an area that does not exceed the verification reference lines 41 and 42, and the non-hatched portion is an area that exceeds the verification reference lines 41 and 42. Become. For the part that is not shaded,
The starting point of altitude calculation changes as compared with the case where the verification reference lines 41 and 42 are not used (when the verification reference lines are not exceeded).
That is, as shown in FIG. 14, in the primary area 11, an area (verification reference line 41, 42 that exceeds the verification reference lines 41, 42) is exceeded.
42 and the area beyond the line segment XY), the starting point is the point Z
Is set to. Therefore, the altitude in this area is
It is calculated based on the shortest distance obtained from a straight line extending radially from the point Z to each calculation point. However, for the area beyond the verification reference lines 41, 42, the altitude at the starting point is higher than the altitude at the above points X, Y, Z (altitude at points X, Y, Z when the verification reference line is not used + 250FT ).

Then, as shown in FIG. 14, the secondary areas 21 and 22 beyond the verification reference lines 41 and 42 (the unshaded areas of the secondary areas 21 and 22 in FIG. 13) are set at the starting points. A gradient of 15: 1 from the primary area 11 obtained as Z is obtained in the same manner as described with reference to FIGS. 8 to 10. However, there are some exceptions described below.

Regarding the shaded area in FIG. 13,
Basically, it is the same as when the verification reference line is not used.
However, as shown in FIG. 15, the secondary area 21 in the portion in contact with the verification reference line 42 is partially irregular and the starting point changes. That is, when the intersection point of the line segment UW which is the outline of the primary area 11 and the verification reference line 42 is defined as a point P1, it is surrounded by the perpendicular line drawn from the line segment UW starting from the point P1 and the verification reference line 42. For the area, the point Z and the point P1 are to be the starting points for altitude calculation.

A specific example of the altitude calculation using the verification reference line will be described with reference to FIG. First, the altitude of the obstacle-free surface 10 at the position of the point E corresponding to an obstacle to be verified in FIG. 16 is calculated.

As a prerequisite, the altitude at point Z is 55
0FT (300 + 250FT), line segment E-P2 = 1.1
NM = 6684FT, shortest distance from point P2 to point Y =
16NM = 97228 FT, primary section 11 slope 4
The gradient is 0: 1 and the secondary sections 21 and 22 have a gradient of 15: 1. The calculation of the obstacle-free surface height under this condition is as follows. Altitude of obstacle-free surface at point E = (6684 ÷ 15) +
(97228 ÷ 40) + 550 = 3426FT.

Next, the altitude of the obstacle-free surface 10 at the position of the point F corresponding to another obstacle to be verified in FIG. 16 is calculated. As a prerequisite, altitude at point Z: 300F
T, line segment F-P1 = 2NM = 12153FT, shortest distance from point P1 to point Z = 10NM = 60767FT, primary zone 11 slope 40: 1, secondary zone 21 slope 15:
Set to 1. The calculation of the obstacle-free surface height under this condition is as follows. Altitude of obstacle-free surface at point F = (1215
3 ÷ 15) + (60767 ÷ 40) + 300 = 2629
FT.

(4) Next, the exception of the starting point of the secondary area will be described. In FIG. 17, the shaded area is the secondary area 22 beyond the verification reference line 42, but there is no primary area 11 beyond the verification reference line 42. In this case,
Even in the secondary area 22, the altitude of the obstacle-free surface is calculated based on the shortest distance from the obstacle to the point Z. However, the gradient is 15: 1.

(5) Next, the straight approach double-pass area will be described. As shown in FIG. 18, the straight approach double-pass area is defined by the runway 2 as an airspace pattern of the return route.
After passing through, the airspace has a pattern for turning straight after going straight for a while. In this case there is no secondary zone. The slope of the obstacle-free surface 12 in the straight line portion is 4
It is 0: 1. In this case, the obstacle-free surface 13 of the turning portion
The range 14 is a portion beyond the verification reference line 43.

An example of calculating the altitude of the obstacle-free surface 12 at the position of the point G corresponding to an obstacle will be described with reference to FIG. As a precondition, the altitude at the line segment MN is 300 FT, the length of the straight line L1 = 3 NM = 18
230 FT, linear section slope 40: 1. In this case, the calculation of the obstacle-free surface height is as follows. Altitude of obstacle-free surface corresponding to point G = (18230 ÷ 40) +
300 = 755 FT.

As described above, the air space setting standard to be processed by the present embodiment may be that the surface of an obstacle is divided into a primary area and a secondary area having different slopes, or there is no secondary area. There is a case where the verification reference line is used and a case where it is not used (when it exceeds or does not exceed), and the starting point of the altitude calculation changes depending on the conditions. It is necessary to select the calculation formula according to the condition of.

For example, altitude calculation (drawing) of an obstacle-free surface
Can be performed by obtaining the altitude corresponding to the coordinates of each intersection that divides the return air space into a mesh shape of a predetermined size. In this case, as one method, for each intersection, first calculate the calculation condition based on the coordinate information as to which condition is used to calculate that point, and then perform the actual altitude calculation based on the calculated calculation condition. Can be considered. Here, the calculation conditions are conditions such as where to set the starting point, how to calculate the distance to the starting point, and what the gradient becomes. However,
In order to calculate the calculation condition of a certain coordinate, it may be necessary in advance to perform similar processing for other coordinate points to calculate the calculation condition and altitude. Further, for these other coordinate points, information on other coordinate points may be required. In such a case, a plurality of calculations using different calculation formulas for the same coordinate point may be repeated, which may require a huge amount of calculation. Therefore, in the present invention, the processing can be simply performed.

The dividing means 103 shown in FIG. 1 is a characteristic part of the present invention. In the dividing means 103, first, in the height calculation of the obstacle-free surface, regions having different starting points can be calculated by the same calculation formula (function). This makes it possible to reduce the number of regions to be divided.

For example, when the verification reference line is not exceeded as shown in FIGS.
A function for calculating the shortest distance to the line segment XYZ in FIG. 7 (a function for calculating the shortest distance to the two line segments) is used.
In this case, since the gradient is the same, 40: 1, the same area is conventionally divided into three regions using three different calculation formulas, but in the present embodiment, these are calculated as one calculation formula. Can be handled as one area that can be calculated in.

When the verification reference line is not exceeded as shown in FIGS. 8 to 10, the secondary areas 21 and 22 are also provided with a function for calculating the shortest distance to the line segment UWV, for example. The divided area was reduced. In this case, since the gradient is the same, 15: 1, it can be handled as one calculation area.

Further, as shown in FIG. 11, the secondary area 2
Regarding points C and D whose starting points are different depending on the primary area 11 inscribed in 1, 2, when the shortest distance to the two line segments is calculated in the secondary areas 21 and 22, the coordinates on the line segment are calculated at the same time. Then, the calculated coordinates are passed to the function for calculating the shortest distance to the line segment XYZ to solve the problem.

Even when the verification reference line is used as a boundary,
As shown in FIG. 19, since the area 52 is the shortest distance to the line segment U-P1 and the area 53 is the shortest distance to the line segment P1-WV, the calculation should be performed in the same way as above. did.

As a result of reducing the number of calculation areas by the above-mentioned methods (1) to (8), the following eight area divisions (area divisions or categories) for calculating the height of the obstacle-free surface are performed. (8 categories).

Category 1: A straight line double-pass section (see FIG. 18)
reference). Category 2: Special area (a special area (for example, area 54 shown in FIG. 19) that occurs due to conditions provided in a part of the primary area). Category 3: Primary area that does not exceed the verification reference line. Category 4: Secondary area outside the turning line that does not exceed the verification reference line. Category 5: Secondary area within a turn that does not exceed the verification reference line. Category 6: Primary area that exceeds the verification reference line. Category 7: Secondary area on the inside of the turn beyond the verification reference line. Category 8: Secondary area outside the turning reference line.

The calculation formulas applied to each category in that case are the calculation formulas A to A for calculating the shortest distance to a predetermined reference line segment or reference point performed in each category.
When the calculation formula G is put, it can be defined as shown in FIG. That is, the area classified into the category 1 can be calculated by the calculation formula A + MDA (FT) -250FT for calculating the shortest distance in the category. Here, MDA is an assumed altitude at the point where the aircraft gives up on landing and starts approaching and retreat, and 250FT is a fixed value. Calculation of the area classified in category 2
(No. 1) When category 1 does not exist: Calculation formula B + M
DA (FT) -250FT can be performed, and (No. 2) category 1 exists: calculation formula B + calculation formula A +
It can be performed with MDA (FT) -250FT. Here, the calculation shown as calculation formula B + calculation formula A first calculates the shortest distance in category 2 using calculation formula B for a certain coordinate point, and the coordinate information of the shortest distance obtained as a result (category information) (Coordinate information of contact point with 1) is given to the calculation formula A set in the category 1, the result of the calculation formula A is obtained, and the information indicating the altitude obtained as the calculation result of the calculation formula A is calculated from the calculation formula B. This means that the altitude corresponding to the coordinate point is obtained by adding the obtained information indicating the altitude.

The calculation of the area classified in category 3 is performed by
(No. 1) When category 1 does not exist: Calculation formula C + M
DA (FT) -250FT can be performed, and (No. 2) category 1 exists: calculation formula C + calculation formula A +
It can be performed with MDA (FT) -250FT. Here, the calculation shown as calculation formula C + calculation formula A first calculates the shortest distance in category 3 using calculation formula C for a certain coordinate point, and the coordinate information corresponding to the shortest distance obtained as a result. Is added to the calculation formula A set in category 1, and the information indicating the altitude obtained as the calculation result of the calculation formula A is added to the information indicating the altitude obtained as the result of the calculation formula C, It means to find the altitude corresponding to.

The calculation of the area classified in category 4 is performed by
Calculation formula D + calculation formula C + MDA (FT) -250FT can be used. That is, for category 4, the shortest distance in a category 4 is calculated for a coordinate point using the calculation formula D, and the coordinate information that is the shortest distance obtained as a result is used as the calculation formula C set for the category 3. The information indicating the altitude obtained as the calculation result of the calculation formula C is added to the information indicating the altitude obtained as the result of the calculation formula D,
Further, it means that the altitude of the coordinate point is obtained by adding MDA and subtracting a fixed value. Note that FIG.
If category 4 exists as shown in 8, category 1 does not exist.

In the same manner, the calculation of the area classified into category 5 is performed by the calculation formula E + calculation formula C + MDA (FT).
It can be done at -250 FT. The calculation of the area classified into the category 6 is performed by the calculation formula F + MDA (FT) -25.
It can be done at 0FT. The calculation of the area classified into the category 7 can be performed by (part 1) if the category 1 does not exist: the calculation formula G + MDA (FT) -250FT, and (part 2) if the category 1 exists: the calculation formula H + The calculation formula F + MDA (FT) -250FT can be used. The calculation of the area classified into the category 8 can be performed by the calculation formula I + calculation formula F + MDA (FT) -250FT.

Further, in the calculation formula of each category,
It is possible to add addition / subtraction for adding or subtracting a predetermined constant.

Here, FIG. 3 shows an example in which neither the primary area nor the secondary area exceeds the verification reference line, and FIG. 1 shows an example in which the turning outer secondary area exceeds the verification reference line.
FIG. 18 showing an example in which a straight traveling portion is included, and an example in the case where all of the turning outer secondary area and part of the primary area and part of the turning inner secondary area exceed the verification reference line. A specific example of the areas classified into each category will be described with reference to FIG.

In the case shown in FIG. 3, there are no areas classified into categories 1-2 and categories 6-8. Category 3 ~
In 5, the respective areas 11, 21, 22 are directly classified.

In the case shown in FIG. 17, there are no areas classified into categories 1 to 2, category 6 and category 8. In the categories 3, 4, and 5, the areas 11 and 21 and the area 22 are included.
Areas that do not exceed the verification reference line 42 (the shaded portion of the area 22) are classified. And category 7
In addition, the area beyond the verification reference line 42 of the area 22 (area 22
The shaded part of) is classified.

In the case shown in FIG. 18, the area 12 is classified into category 1. What is classified into category 3 is a portion of the area 13 excluding the range 14. Area 13 is classified into category 6 in category 6.
Of the range 14 of the above.

In the case shown in FIG. 19, there are no areas classified into categories 1 and 5. Area 54 is in category 2, and areas 5 are in categories 3, 4, 6, 7, and 8.
6, 52, 57, 22 and 53 are classified.

Next, each calculation formula A to calculation formula I shown in FIG.
A specific example of is as shown in FIG. Here, the gradient of the primary zone is 40: 1 and the gradient of the secondary zone is 15: 1.

The calculation formula A is, for example, (the shortest distance from the obstacle to the line segment MN in FIG. 18) ÷ 40. The calculation formula B is (the shortest distance from the obstacle to the line segment 55 in FIG. 19) ÷ 15. The calculation formula C is (FIG. 3, FIG. 17, FIG. 18 or FIG.
And the shortest distance from the obstacle to the line segment XYZ or X1-Y1-Z1) ÷ 40. Calculation formula D is (from the obstacle,
Is the shortest distance to the line segment UWV and the line segment U-P1 in FIG. 19) ÷
It is 15. The calculation formula E is (the shortest distance from the obstacle to the line segment formed by the tangent line between the area 11 and the area 22 in FIG. 3 or 17) ÷ 15.

The calculation formula F is (from the obstacle, point Z in FIG.
1, the shortest distance to the point Z in FIG. 19) ÷ 40. The calculation formula G is (the shortest distance from the obstacle to the point Z in FIG. 17) ÷ 15.
Is. The calculation formula H is (the shortest distance from the obstacle to the line segment consisting of the tangents to the areas 11 and 22 in FIG. 19) ÷ 15. Then, the calculation formula I is (the line segment P from the obstacle in FIG.
1-WV shortest distance) ÷ 15.

Further, the dividing means 11 in FIG. 1 uses the method of dividing each area into polygons (polygonal surfaces) of drawn parts instead of the conventional determination of route setting conditions and intersections of line segments. We have adopted the method of classifying. Specifically, each part of the primary area and the secondary area is recognized as one polygon, and the primary area, the secondary area (inside), and the secondary area (outside) of the protected airspace registered by the condition input unit 101 are recognized. The intersection with the verification reference point is calculated based on each vertex coordinate, each area is divided by the verification reference line based on the calculated intersection information, and the vertex coordinates of each divided area are stored in the storage area for each category. To store. At this time, for the secondary area, it is necessary to obtain information about which line segment or point the shortest distance should be obtained,
The verification basic line segment information in the secondary area is stored together with the coordinate points of the shape information related to the protected airspace. For example, in the example of FIG. 19, the coordinates forming the line segment U-P1 are stored in the category 4, and the coordinates of the line segment P1-WV are stored in the category 8 at the same time.

Then, the judging means 104 calculates the altitude at the mesh intersection point in each area based on the calculation formula set in each category. Then, the map altitude data of the verification target or the like which is registered in advance by the verification target information input means 102 is read, and it is judged whether or not there is an obstacle by comparing it with the altitude calculated above.

A specific verification example will be described for an obstacle located at a point E shown in FIG. In this case, the point E corresponding to the obstacle is the verification reference line 42 classified into the category 8.
It will be located in the turning outer secondary area 53 beyond.
The calculation process of the obstacle-free surface height is as follows.

It is determined which category the coordinate point E corresponding to the obstacle belongs to.

When it is determined that the point E of the obstacle belongs to the category 8, the shortest distance to the secondary area verification basic line segment information (line segment P1-WV) stored in the category 8 and the coordinate point. A process of calculating P2 is performed (calculation formula I in FIG. 22).

An increase in altitude in the secondary area is calculated from the distance obtained above and the gradient of 15: 1 (calculation formula I in FIG. 22).

The shortest distance from the coordinate point P2 to the point Z is calculated, and the increase in altitude in the primary area 57 is calculated from the gradient of 40: 1 (calculation formula F in FIG. 22).

The increase in altitude in the secondary area 53 obtained in step 3 and the increase in altitude in the primary area 57 obtained in step 1 are added, and the altitude at the starting point is calculated using the MDA value and a predetermined fixed value. Then, the height of the obstacle-free surface at the point E is calculated.

The altitude of the obstacle-free surface at the point E obtained in (1) and the altitude of the obstacle are compared and verified.

The processing flow of the entire system is as follows. (1) Input route installation conditions, (2)
Drawing of shape (protected airspace), (3) Topography around protected airspace
Extraction of artificial obstacles, (4) Divide the drawn protective airspace into categories according to the calculation conditions for the surface of no obstacles. (5)
For each of the obstacles extracted in (3), the inside / outside determination is performed one by one as to whether or not they are in the protected airspace, and the process is repeated until the determination is completed for all the extracted obstacles.

The embodiment of the present invention is not limited to the above-mentioned one. For example, the respective means of FIG. 1 may be dispersed and configured via a network, or the respective means may be integrated, or other means. Modifications such as combining with conventional functions can be appropriately made. A program for executing each function in the computer configuring FIG. 1 can be distributed via a computer-readable recording medium or a communication line.

[0070]

As described above, according to the present invention, the automation of verification can be promoted, and the verification of obstacles can be carried out accurately and quickly, and the work efficiency of the designer is improved. In particular, the route design becomes easy when the verification range includes a plurality of obstacles.

[Brief description of drawings]

FIG. 1 is a block diagram showing a configuration of an embodiment of an airspace design support system of the present invention.

FIG. 2 is a plan view of an unobstructed surface 1 to be processed by the embodiment of FIG. 1 as seen from above.

FIG. 3 is a plan view similar to FIG.

FIG. 4 is a side view corresponding to the plan view of FIG.

5 is a plan view for explaining the starting point of altitude calculation in the primary area 11 of FIG. 2. FIG.

FIG. 6 is another plan view for explaining the starting point of altitude calculation in the primary area 11 of FIG.

7 is still another plan view for explaining the starting point for calculating the altitude of the primary area 11 of FIG. 2. FIG.

8 is a plan view for explaining a starting point of altitude calculation in the secondary area 21 of FIG. 2. FIG.

9 is another plan view for explaining the starting point for calculating the altitude of the secondary area 21 in FIG. 2. FIG.

FIG. 10 is still another plan view for explaining the starting point of the altitude calculation of the secondary area 21 of FIG.

FIG. 11 is a plan view for explaining a specific example of altitude calculation in the secondary area 21 of FIG.

FIG. 12 is a plan view for explaining a verification reference line for the obstacle-free surface 1 to be processed by the embodiment of FIG.

13 is a plan view for explaining a verification reference line 42 of FIG.

14 is a plan view for explaining an example of altitude calculation in the primary area 11 using the verification reference line 42 of FIG.

15 is a plan view for explaining an example of altitude calculation in the secondary area 21 using the verification reference line 42 of FIG.

16 is a plan view for explaining a specific example of altitude calculation in the primary area 21 using the verification reference line 42 of FIG.

17 is a plan view for explaining a special case of altitude calculation processing using the verification reference line 42 of FIG.

FIG. 18 is a plan view showing an example of a straight approach double-pass area which is a processing target in the present embodiment.

19 is a plan view for explaining a specific example of altitude calculation processing using the verification reference line 42 of FIG.

20 is a chart showing a list of categories set by category division by the dividing means 103 in FIG. 1. FIG.

21 is a chart showing a list of calculation formulas for altitude calculation in each category shown in FIG. 20. FIG.

22 is a chart showing a specific example of each calculation formula shown in FIG. 21. FIG.

[Explanation of symbols]

1 Unobstructed surface 41, 42, 43 Verification reference line 101 Non-obstacle surface calculation condition input means 102 verification object information input means 103 dividing means 104 determination means 105 output means

   ─────────────────────────────────────────────────── ─── Continued front page    (72) Inventor Kengo Watanabe             Stock Exchange, 3-3 Toyosu 3-chome, Koto-ku, Tokyo             Company NTT Data F-term (reference) 5H180 AA26 EE01 EE02 LL01

Claims (3)

[Claims] 1. In a protected area of a flight path of an aircraft,
For verifying the presence or absence of obstacles on an obstacle-free surface that includes two or more planes with different slopes and is calculated under a plurality of different conditions with a verification reference line serving as a reference for verification of obstacles as a boundary. The system is a first input means for inputting calculation conditions for an obstacle-free surface, a second input means for inputting information indicating one or more verification objects, and an obstacle-free surface as a verification standard. A dividing means for dividing each polygonal surface into gradients based on a line, an altitude of an obstacle-free surface calculated using a plurality of calculation formulas defined for each divided polygonal surface, and the verification target An airspace design support system comprising: a determination unit that compares the altitude of an object to determine whether or not there is an obstacle, and an output unit that outputs a determination result regarding the presence or absence of an obstacle. 2. Each of the calculation formulas defined for each polygonal surface is based on the altitude of each point of the polygonal surface, based on one or a plurality of continuous line segments or one point on the outer periphery of each polygonal surface. 2. The multiplication / division operation for multiplying the shortest distance obtained as the above by a gradient and a predetermined addition / subtraction operation.
Airspace design support system described. 3. In the protected airspace of the flight path of the aircraft,
Use a computer to determine the presence or absence of an obstacle for an obstacle-free surface that includes two or more planes with different slopes and is calculated under a plurality of different conditions with a verification reference line serving as a reference for verification of an obstacle as a boundary. A method for verification, comprising a first step of inputting calculation conditions for an obstacle-free surface, a second step of inputting information indicating one or a plurality of verification objects, and verification of an obstacle-free surface. The height of the obstacle-free surface is compared with the height of the verification target object for each polygonal surface divided into multiple slopes with the reference line as the boundary, and the comparison result is output as the judgment result of the presence or absence of the obstacle. And a third step of performing an airspace design support method.