CN111792054A - Safe test flight method based on airplane airborne sliding forced landing capability - Google Patents
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Abstract
The invention discloses a safe test flight method based on airplane airborne sliding forced landing capacity, which comprises a safe area, wherein an airplane is in unpowered safe return forced landing in the safe area; drawing a security domain circle by taking the coordinate of the center of the second spiral circle as the center of the circle and the difference between the radius of the coordinate circle of the center of the first spiral circle and the radius of the first spiral circle as the radius; the safety domain circle forms a safety domain of the airplane to slide from one side of the airport runway to land forcibly under the unpowered condition. The invention solves the problem of flight risk management and control of the test flight department which easily causes aerial parking, ensures that the aircraft can safely return to the ground and forcedly land under the unpowered condition once the aerial parking special condition occurs in the area, and ensures the safety of pilots and the aircraft.
Description
Technical Field
The invention belongs to the technical field of airplane test flight, and particularly relates to a safe test flight method based on airplane forced landing capability during airborne sliding.
Background
The aircraft engine serving as a power source of the aircraft provides thrust or torque required by power for aircraft flight, and provides hydraulic pressure, air entraining, power supply and the like for the aircraft through a transmission accessory, and the aircraft engine is the key for ensuring normal flight of the aircraft. During flight, the flight risk of the aircraft is greatly increased once an aerial stop occurs and the aerial launch fails. In the stage of new aircraft development and test flight, aiming at the risk subjects which are easy to cause the engine to stop in the air at present, the risk subjects are basically tested flight tasks after air slide forced descent drilling.
The air-parking risk management and control of the trial flight department mostly depends on the driving technique and psychological quality of pilots, the flight level of ground commanders and related special situation handling experience, and the flight risk management and control uncertainty exists in the general view. The invention provides a safe area for trial flight of an idle stop risk subject based on the idle sliding forced landing capability of the airplane, and ensures that the airplane is in unpowered safe return forced landing in the area.
Disclosure of Invention
The invention aims to provide a safe test flight method based on airplane idle-skid forced landing capacity, and aims to solve the problem of flight risk management and control of test flight subjects which are easy to cause air parking, ensure that once the airplane is parked in the area specially, the airplane can safely return to the ground and be forced to land under the unpowered condition, and ensure the safety of pilots and airplanes.
The invention is mainly realized by the following technical scheme: a safe test flight method based on airplane airborne sliding forced landing capability comprises a safe area, wherein an airplane does not need power and is safely returned to the ground to be forced to land in the safe area; forced landing route of airplane after parking in air: firstly, stably circling around a first circling circle and adjusting the course to align to an airport, linearly sliding down at a constant speed towards the airport, then stably circling around a second circling circle and adjusting the course to align to the runway of the airport to prepare for landing, wherein the straight gliding section of the airplane is a common tangent line of the first circling circle and the second circling circle, and the length of the straight gliding section is l; establishing a two-dimensional plane coordinate system by taking the direction of the airport runway as an abscissa and the direction vertical to the airport runway as an ordinate and taking the center of the airport runway as an origin of coordinates; the radiuses of the first spiral circle and the second spiral circle are R and R respectively;
second spiralCenter coordinates (x) of circle1,y1) The equation of the circle of the second convolution is (x-x)1)2+(y-y1)2＝r2；
The center coordinate of the first spiral circle is (x)2,y2) That is, the center coordinates of the first spiral circle satisfying the condition are circumscribed circle (x-x)1)2+(y-y1)2＝l2+(R-r)2And inscribed circle (x-x)1)2+(y-y1)2＝l2+(R+r)2A point on;
selecting (x-x)1)2+(y-y1)2＝l2+(R-r)2And (x-x)1)2+(y-y1)2＝l2+(R+r)2A circle with a smaller middle radius is used as a circle center coordinate circle of the first spiral circle; drawing a security domain circle by taking the coordinate of the center of the second spiral circle as the center of the circle and the difference between the radius of the coordinate circle of the center of the first spiral circle and the radius of the first spiral circle as the radius; the safety domain circle forms a safety domain of the airplane to slide from one side of the airport runway to land forcibly under the unpowered condition.
In order to better implement the method, the height of the landing longitudinal glide starting point in the airplane forced landing process is further assumed to be h1And is l from the center of the airport runway1The height and the surface speed of the starting point of the flight direction adjustment of the airplane in the forced landing process of the airborne skidding are respectively h2V, the air-slip ratio corresponding to the aircraft gauge speed is k;
potential energy height delta h which can be used in the process of forced landing of aircraft during air sliding after parking in the air2-h1(ii) a Assuming that the respective lost heights of one circle of circling are respectively delta h when the airplane is in idle sliding forced landing1And Δ h2(ii) a The available potential energy height delta h' ═ delta h-delta h of the airplane gliding straight at the same speed1-Δh2(ii) a The horizontal flight distance l of the plane gliding in a straight line at a constant speed is k.DELTA h'.
In order to better implement the invention, further, the aircraft unpowered airborne landing process comprises stable hovering descent and constant-speed linear gliding flight motion.
In order to better realize the method, a safety domain of the aircraft landing forced landing from the idle slipping at two ends of the runway of the airport under the condition of no power is obtained in the same way.
The invention has the beneficial effects that:
the invention solves the problem of flight risk management and control of the test flight department which easily causes aerial parking, ensures that the aircraft can safely return to the ground and forcedly land under the unpowered condition once the aerial parking special condition occurs in the area, and ensures the safety of pilots and the aircraft.
Drawings
FIG. 1 is a schematic diagram of an airborne forced landing process under no power condition of an aircraft;
FIG. 2 is a schematic diagram of a coordinate system of an airplane airborne slide forced landing route;
FIG. 3 is a circle center coordinate circle of the aircraft idle-sliding forced landing circling circle 1;
FIG. 4 is a schematic diagram of a construction of a flight test security domain of an airplane during an idle-skid forced landing;
FIG. 5 is a schematic diagram of a safety domain of airplane forced landing test flight;
fig. 6 is a schematic diagram of a safety domain of airplane forced landing for test flight.
Detailed Description
Example 1:
a safe test flight method based on airplane airborne sliding forced landing capability comprises a safe area, wherein an airplane does not need to be safely returned to the ground to be forced to land in the safe area. The method mainly comprises the following steps:
1) the airborne forced landing process of the aircraft under unpowered condition is shown in figure 1.
2) The unpowered air-sliding forced landing process of the airplane is simplified into two flight motions of stable hovering descent and constant-speed linear gliding descent.
3) Without loss of generality, in the forced landing route of the airplane after parking in the air, the stable circle (circle 1) is firstly adjusted to align the course to an airport, then the airplane linearly glides at a constant speed towards the airport, then the stable circle (circle 2) is adjusted to align the course to an airport runway for landing, the path of the straight gliding segment of the airplane is exactly the common tangent line of the two stable circles, and a plurality of important points on the route are respectively represented by 1, 2, 3, 4 and 5, as shown in fig. 1 and 2.
4) A two-dimensional plane coordinate system is established by taking the airport runway direction as an abscissa, the direction perpendicular to the airport runway as an ordinate and taking the airport runway center point as an origin of coordinates, as shown in fig. 2.
5) Suppose that the height of 2 points in the aircraft idle sliding forced landing process in 3) is h1Distance from the center of the runway is l1The height and the gauge speed of the airplane at 5 points in 3) are respectively h2And V, the aircraft gauge speed V corresponds to an air-to-slip ratio of k.
6) Potential energy height delta h which can be utilized in the process of forced landing of aircraft during air sliding after parking in the air2-h1。
7) Assuming that when the airplane is forced to land by idle sliding, the circling radiuses for stabilizing circling by twice adjusting the course are respectively R and R, and the respective lost height of a circle of circling is respectively delta h1And Δ h2。
8) Available potential energy height delta h ═ delta h-delta h of airplane constant-speed linear gliding1-Δh2。
9) The horizontal flight distance l of the plane gliding in a straight line at a constant speed is equal to k · Δ h', namely the length of a common tangent line of the circle 1 and the circle 2 is l.
10) From 4), 5), and 7), the center coordinates (x) of the spiral circle 2 can be obtained1,y1)。
11) According to 7) and 10), the equation of the circle of the spiral circle 2 can be obtained as (x-x)1)2+(y-y1)2＝r2。
12) According to the equation (x-x) for the circle 2 in 7) the radius R of the circle 1, 9) the length l of the tangent line common to the circle 1 and the circle 2, 11)1)2+(y-y1)2＝r2The center coordinates (x) of the spiral circle 1 can be obtained2,y2) As shown in FIG. 3, the center coordinates of the spiral circle 1 satisfying the condition are a circle (x-x)1)2+(y-y1)2＝l2+(R-r)2(exo) and (x-x)1)2+(y-y1)2＝l2+(R+r)2(inscribing) a point.
13) Selecting a circle (x-x)1)2+(y-y1)2＝l2+(R-r)2And (x-x)1)2+(y-y1)2＝l2+(R+r)2The circle with smaller middle radius is used as the coordinate circle of the center of the circle 1.
14) And (4) drawing a circle 3 by taking the coordinate of the center of the circle 2 of the spiral circle 11) as the center of the circle and the difference between the radius of the circle 1 of the center of the circle coordinate circle and the radius of the circle 1 of the spiral circle as the radius.
15) The area enclosed by the circle 3 forms a safety domain for the airplane to slide from one side of the runway of the airport to land under the condition of no power, as shown in figure 4.
16) According to the method, the safety domain of the airplane to land and land from the two sides of the runway of the airport under the condition of no power can be obtained by the same method, as shown in figure 5.
17)16) together constitute a test flight security domain (shaded area) of the aircraft based on airborne forced landing, as shown in fig. 6.
18) If the landing direction of the runway of the airport is specified, such as the landing from the left end to the right of the runway azimuth shown in fig. 6, the local safety domain range can be further displayed, as shown by the dotted circle in fig. 6.
The invention solves the problem of flight risk management and control of the test flight department which easily causes aerial parking, ensures that the aircraft can safely return to the ground and forcedly land under the unpowered condition once the aerial parking special condition occurs in the area, and ensures the safety of pilots and the aircraft.
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 (4)
1. A safe test flight method based on airplane airborne sliding forced landing capability is characterized by comprising a safe area, wherein an airplane is in unpowered safe return forced landing in the safe area; forced landing route of airplane after parking in air: firstly, stably circling around a first circling circle and adjusting the course to align to an airport, linearly sliding down at a constant speed towards the airport, then stably circling around a second circling circle and adjusting the course to align to the runway of the airport to prepare for landing, wherein the straight gliding section of the airplane is a common tangent line of the first circling circle and the second circling circle, and the length of the straight gliding section is l; establishing a two-dimensional plane coordinate system by taking the direction of the airport runway as an abscissa and the direction vertical to the airport runway as an ordinate and taking the center of the airport runway as an origin of coordinates; the radiuses of the first spiral circle and the second spiral circle are R and R respectively;
center coordinates (x) of the second spiral circle1,y1) The equation of the circle of the second convolution is (x-x)1)2+(y-y1)2＝r2；
The center coordinate of the first spiral circle is (x)2,y2) That is, the center coordinates of the first spiral circle satisfying the condition are circumscribed circle (x-x)1)2+(y-y1)2＝l2+(R-r)2And inscribed circle (x-x)1)2+(y-y1)2＝l2+(R+r)2A point on;
selecting (x-x)1)2+(y-y1)2＝l2+(R-r)2And (x-x)1)2+(y-y1)2＝l2+(R+r)2A circle with a smaller middle radius is used as a circle center coordinate circle of the first spiral circle; drawing a security domain circle by taking the coordinate of the center of the second spiral circle as the center of the circle and the difference between the radius of the coordinate circle of the center of the first spiral circle and the radius of the first spiral circle as the radius; the safety domain circle forms a safety domain of the airplane to slide from one side of the airport runway to land forcibly under the unpowered condition.
2. The safe test flight method based on the airplane forced airborne sliding capability of claim 1, wherein the height of the landing longitudinal glide starting point in the airplane forced airborne sliding process is assumed to be h1And is l from the center of the airport runway1The height and the surface speed of the starting point of the flight direction adjustment of the airplane in the forced landing process of the airborne skidding are respectively h2V, the air-slip ratio corresponding to the aircraft gauge speed is k; potential energy height delta h which can be used in the process of forced landing of aircraft during air sliding after parking in the air2-h1(ii) a Suppose an aircraft is in the airWhen sliding and forced landing, the respective lost height of one circle of the circle is delta h1And Δ h2(ii) a The available potential energy height delta h' ═ delta h-delta h of the airplane gliding straight at the same speed1-Δh2(ii) a The horizontal flight distance l of the plane gliding in a straight line at a constant speed is k.DELTA h'.
3. The safe test flight method based on the airplane forced airborne capability of claim 1, wherein the unpowered forced airborne process of the airplane comprises stabilizing the flying motion of hovering descent and constant-speed linear glide.
4. A safe test flight method based on airplane forced airborne capability according to any one of claims 1-3, characterized by obtaining the safety domain of forced airborne landing from both sides of airport runway under the condition of no power of airplane in the same way.
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| CN113139234A (en) * | 2021-03-31 | 2021-07-20 | 成都飞机工业（集团）有限责任公司 | Flight energy effective conversion method for relatively optimal air-slip ratio |
| CN113190024A (en) * | 2021-03-31 | 2021-07-30 | 成都飞机工业（集团）有限责任公司 | Decision and guidance method for forced landing of airborne sliding of manned fixed wing aircraft |
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| CN116736747A (en) * | 2023-08-15 | 2023-09-12 | 陕西德鑫智能科技有限公司 | Unmanned aerial vehicle emergency treatment method and device |
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| CN116736747A (en) * | 2023-08-15 | 2023-09-12 | 陕西德鑫智能科技有限公司 | Unmanned aerial vehicle emergency treatment method and device |
| CN116736747B (en) * | 2023-08-15 | 2023-11-14 | 陕西德鑫智能科技有限公司 | Unmanned aerial vehicle emergency treatment method and device |
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