CN110733664A - seaplane takeoff performance verification method - Google Patents
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- CN110733664A CN110733664A CN201910931096.6A CN201910931096A CN110733664A CN 110733664 A CN110733664 A CN 110733664A CN 201910931096 A CN201910931096 A CN 201910931096A CN 110733664 A CN110733664 A CN 110733664A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
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Abstract
The invention belongs to the field of airplane design, is suitable for air hydraulic design of a water surface airplane, an amphibious airplane and a water surface high-speed moving body, and relates to methods for verifying takeoff performance of a seaplaneGWWhen the water craft is in use, the pull rod raises to keep the attitude of the water craft within a stable range, and the soaring speed V is achievedLOFWWhen the airplane completely leaves the water but flies close to the water surface, the speed reaches VEFWA critical engine stop is made and then accelerated to a decision speed V1WAnd continuously accelerates to the head-up speed VRWWhen the pull rod is raised, the airplane climbs to a safe height, and the flying speed is not less than the safe speed V at the moment2And then continue climbing. The method for verifying the takeoff performance conformity of the seaplane provides a basis for the design of the seaplane to meet the safety standard by determining the flight path and the characteristic speed of each segment.
Description
Technical Field
The invention belongs to the field of airplane design, is suitable for air-water power design of a water surface airplane, an amphibious airplane and a water surface high-speed moving body, and relates to a method for verifying takeoff performance of kinds of seaplanes.
Background
The amphibious aircraft has the characteristics that the process of taking off the water surface and the process of taking off the water surface have completely different characteristics from the process of taking off the water surface on a ground runway, the aircraft is under the combined action of static buoyancy, hydrodynamic force and aerodynamic force when taking off the water surface, and the three acting forces can change greatly along with the change of the flying speed.
In operation, the greatest difference between the take-off process of an amphibious aircraft from the water and the ground is that the aircraft has landing gear support when taking off from the ground, and the pilot can control the aircraft not to lift head to take off before reaching the speed of the front wheel lift by operating the control surface, and the pilot pulls the mast to take off after reaching the speed of the front wheel lift, while when the aircraft takes off from the water, the aircraft is made to increase and then decrease in the water surface taxiing attitude due to the constant change of the force to which the aircraft is subjected, and a distinct trim peak occurs.
Therefore, the terms of the take-off speed requirement of the land-based aircraft in the pilot law CCAR-25-R4 are not completely applicable to take-off of the seaplane on the water surface, and the relevant requirements of the seaplane or the amphibious aircraft on the take-off speed on the water surface need to be increased.
Disclosure of Invention
The invention aims to provide verification methods for takeoff performance of a seaplane, and ensure the development and operation safety of the seaplane or an amphibious aircraft.
The technical scheme includes that seaplane takeoff performance verification methods are adopted, and seaplanes are accelerated to reach a water leaving speed V from a static stateGWWhen the water craft is in use, the pull rod raises to keep the attitude of the water craft within a stable range, and the soaring speed V is achievedLOFWWhen the airplane completely leaves the water but flies close to the water surface, the speed reaches VEFWTime critical start requires stopping and then accelerating to decision speed V1WAnd continuously accelerates to the head-up speed VRWWhen the pull rod is raised, the airplane climbs to a safe height, and the flying speed is not less than the safe speed V at the moment2Then must be as close as possible to, but not less than, V2When the speed of the aircraft is continuously climbed to 120 meters, the aircraft is accelerated to a favorable climbing speed, the flap is folded, and the aircraft continuously climbs to a green point height of 450m, namely a water surface takeoff flight path.
The water leaving velocity VGWNot less than the aircraft stall speed.
The flight velocity VLOFWMust not exceed the maximum speed V of the aircraft which can be safely controlled on the water surfaceMAXW。
Soaring speed VLOFWIn the front, the attitude stability range of the seaplane is 3-10 degrees.
When the airplane flies away from water and close to the water, the distance between the bottom of the airplane and the water surface is 0.5-5 m.
When the airplane is stopped by one shot, the water leaving speed VRWThe steady climbing gradient of the steel is not less than 0.5 percent; safe speed V2The steady climb gradient of (a) must not be less than 3%.
The safety height is 10.7 meters.
The slope of the aerial part of the flight path must be positive, starting from the point where the aircraft is 120 m above the takeoff surface, the available climbing gradient at each point along the takeoff path must not be less than 1.7%, the takeoff height of the aircraft is less than 120 m, the form of the aircraft must not be changed except for the automatic feathering of the propeller, the pilot must not take action to change power or thrust, and the flight path must be based on the aircraft performance of the waterless effect.
The water leaving velocity VGWAt 150-200 KM/H.
The flight velocity VLOFWAt 165-220 KM/H.
The invention has the technical effects that: the verification method for the takeoff performance conformity of the seaplane limits the flight speed in the takeoff stage through flight test flight, controls each characteristic speed and flight track, ensures that the seaplane has enough safety during takeoff, and provides a basis for the design safety standard of the seaplane.
Drawings
FIG. 1 is a flight path schematic diagram of the method for verifying the takeoff performance conformity of a seaplane according to the invention.
Detailed Description
The present invention is described in further detail at below.
The invention relates to a verification method for takeoff performance of a seaplane, which is used for accelerating the seaplane from a static state to a water leaving speed V when a sectional test is carried out for flyingGWWhen the water craft is in use, the pull rod raises to keep the attitude of the water craft within a stable range, and the soaring speed V is achievedLOFWWhen the airplane completely leaves the water but flies close to the water surface, the speed reaches VEFWTime critical start-stop, then accelerate to decision speed V1WAnd continuously accelerates to the head-up speed VRWWhen the pull rod is raised, the airplane climbs to a safe height, and the flying speed is not less than the safe speed V at the moment2And then continue climbing. By the verification method, the takeoff safety of the seaplane can be effectively guaranteed, and a basis is provided for airplane design.
The method for verifying the takeoff performance of the seaplane comprises the following steps of dividing each phase and determining each characteristic speed in the method for verifying the takeoff performance of the seaplane, wherein the division of each phase and the determination of each characteristic speed are not absolutely or artificially and subjectively selected, but are determined by combining aviation flight safety standard requirements through flight tests and aerodynamic requirements according to the actual flight condition of the seaplane strictly, so that the requirements are as follows:
1) the segmentation must be well defined and there must be clearly discernable changes in form, power (thrust) and speed;
2) the weight, shape, power (thrust) of the aircraft must remain constant in each segment and must correspond to the most critical conditions prevailing in that segment;
3) flight path must be based on aircraft performance without ground effects;
4) the takeoff trajectory data must be checked for several consecutive demonstrative takeoffs (until the aircraft departs from the ground effect and its speed reaches a stable point) to ensure that the piecewise synthetic trajectory is conservative with respect to the consecutive trajectory.
5) The slope of the aerial portion of the water surface takeoff track must be positive at each point to ensure that the altitude is rising during each takeoff phase.
In a certain embodiment, the verified object is a water amphibious aircraft with a takeoff weight of 50 tons, and in specific implementation, referring to fig. 1, the method for determining the takeoff speed of the water aircraft gives a water surface takeoff flight path in a segmented form, and the specific process is as follows:
step 1: determining a seaplane takeoff speed threshold
Calculating stall speed V according to aerodynamic force, hydrodynamic force and engine of airplaneSThe maximum speed V of the airplane on the water surface can be safely controlledMAXWMinimum operating speed V of water surfaceMCWMinimum operating speed V in the airMCAAnd the maximum speed V of the airplane which can safely stop taking off when taking off on the water surface1WMAXThese speeds are all fixed after the aircraft design is complete and can be determined individually by flight tests to meet flight safety standards. In the present embodiment, stall speed VS140km/h, maximum velocity VMAXW180km/h and the water surface is the highestSmall operating speed VMCW190km/h, minimum operating speed V in the airMCA160km/h, maximum speed V for safely suspended takeoff1WMAXIs 220 km/h.
Step 2: establishing the water leaving velocity VGW
The determination of the leaving velocity V in this example is carried out by flight testsGW160km/h, the water leaving speed is not determined subjectively, but is determined according to the flight aerodynamic condition of the seaplane and the aerodynamic characteristics of the plane by combining with flight tests and researches, and the water leaving speed V needs to meet specific technical requirementsGWThe lower limit satisfies:
VGWstall speed V not less than critical engine failureS140km/h to avoid that the airplane immediately enters stall after leaving water, thereby influencing flight safety;
leaving velocity VGWThe upper limit requirement is not more than the soaring speed VLOFWSo as to avoid the over-high flying speed and reduce the flight control performance and stability;
and step 3: establishing an ascension speed VLOFW
Continuously accelerating to the soaring speed V of the airplaneLOFW165km/h and requires from VGWActual flying speed V of airplane obtained by starting to leave waterLOFWMust not exceed VMAXWTo ensure flight safety, wherein VMAXWThe maximum speed of the airplane which can be safely controlled on the water surface. The plane completely leaves the water but flies close to the water surface, the height from the water surface is 1.5 to 5 meters, and the plane continues to accelerate to reach VEFWA key starting stop is carried out (single stop, the rest of the engine continues to work).
VEFWIs the corrected airspeed, V, assuming a critical engine failure at water takeoffEFWMust be selected by the applicant, but not less than V determined by the surface handling characteristicsMCW190km/h；
And 4, step 4: determining a decision velocity V1W
Accelerating to decision velocity V1W195km/h, wherein the decision velocity V1WMust be according to VEFWMade to meet specific flight requirements and pneumatically operatedThe simulation or flight test determines that the method comprises the following specific steps:
a)V1Wis a predetermined water surface takeoff decision speed expressed by corrected airspeed and satisfies the following requirements:
ⅰ)V1Wmust not be less than VEFWPlus the speed increment at which the critical engine is not operating for the aircraft during the time interval from the instant the critical engine fails to the instant the pilot is aware of the engine failure and reacts, and the latter instant is subject to the oil recovery deceleration measures taken by the pilot in the surface acceleration-stop test;
ⅱ)V1Wmust not exceed V1WMAXWherein V is1WMAXThe maximum speed of the airplane which can safely stop taking off when taking off on the water surface;
and verifying whether the airplane meets the takeoff condition or not when the airplane fails in the takeoff stage, so that the pilot can make a takeoff decision.
And 5: aircraft head-up climbing
Accelerating to the head-up speed V after the airplane determines to continue taking offRW197km/h, the pull rod is raised, VRWThe head-up speed after the plane leaves the water is expressed by a calibrated airspeed, the head-up speed is determined according to the flight aerodynamic condition of the seaplane, and the following technical requirements are required to be met to ensure the flight safety:
a)VRWmust not be less than any of the following speeds:
1)V1W；
2)VLOFW；
3)1.05VMCA；
4)1.03VSR；
5) the speed of the airplane can reach V before the airplane is 10.7 meters (35 feet) higher than the takeoff surface2Certain speed.
b) For any given set of conditions (weight, center of gravity, configuration, temperature and humidity), the same V must be determinedRWValues indicate compliance with both single takeoff and full takeoff conditions.
Under the following conditions VRWMust not be less than0.5％；
c) The critical engine is stopped and the remaining engines are at a speed V as specified by the water takeoff trajectoryRWAvailable power (thrust) state of time;
b) the weight is equal to the speed V specified by the water surface takeoff trackRWWeight per hour.
Step 6: accelerating climbing to a safe height
The airplane climbs to the safe height of 10.7 meters, and the flying speed is not less than the safe speed V at the moment2205km/h at a speed V2Must not be less than 3%:
and 7: continuously climbing to the level flying height
To be as close as possible to but not less than V2When the speed of the aircraft is continuously climbed to 120 meters, then the aircraft is accelerated in a level flight mode, and at the moment, the appearance of the aircraft can be adjusted by operating a flap so as to continuously climb in an accelerated mode;
and 8: continuously climbs to the green point height
And accelerating the horizontal flight to a favorable climbing speed, continuously climbing to the green point height of 450m by operating the lifting rod, and ending the water surface takeoff flight path.
In addition, during the whole takeoff process, the water surface takeoff track is required to extend from a static point to the higher of the following two points: 450 meters (1,500 feet) above the takeoff surface during takeoff of the aircraft, or completing the transition from takeoff to route configuration and reaching VFTOPoint .
The foregoing is merely a detailed description of the embodiments of the present invention, and is not intended to represent the conventional art. The scope of the present invention is not limited thereto, and any changes or substitutions that can be easily made by those skilled in the art within the technical scope of the present invention will be covered by the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (9)
1, seaplane takeoff performance verification method, characterized in that, the seaplane accelerates to get out of water from static stateVelocity VGWWhen the water craft is in use, the pull rod raises to keep the attitude of the water craft within a stable range, and the soaring speed V is achievedLOFWWhen the airplane completely leaves the water but flies close to the water surface, the speed reaches VEFWA critical engine stop is made and then accelerated to a decision speed V1WAnd continuously accelerates to the head-up speed VRWWhen the pull rod is raised, the airplane climbs to a safe height, and the flying speed is not less than the safe speed V at the moment2And then continue climbing.
2. The seaplane takeoff performance verification method as claimed in claim 1, wherein the water leaving speed VGWNot less than the aircraft stall speed.
3. The seaplane takeoff performance verification method as claimed in claim 1, wherein the flight speed VLOFWMust not exceed the maximum speed V of the plane which can be stably controlled on the water surfaceMAXW。
4. The seaplane takeoff performance verification method according to claim 1, wherein the flight speed VLOFWIn the front, the attitude stability range of the seaplane is 3-10 degrees.
5. The method for verifying takeoff performance of a seaplane according to claim 1, wherein when the plane flies away from water and close to water, the distance between the bottom of the plane and the water surface is 0.5-5 m.
6. The seaplane takeoff performance verification method according to claim 1, wherein the departure speed V is set at the time of single-engine parking of the seaplaneRWThe steady climbing gradient of the steel is not less than 0.5 percent; safe speed V2The steady climb gradient of (a) must not be less than 3%.
7. The seaplane takeoff performance verification method according to claim 1, wherein the safe height is 10.7 m, and the flight speed is not less than the safe speed V2Then must be as close as possible to, but not less than, V2When the speed of the robot continuously climbs to 120 meters, the robot carries out level flight acceleration, accelerates to a favorable climbing speed, retracts a flap, and continuously climbs to a green point height of 450 m.
8. The seaplane takeoff performance verification method as claimed in claim 1, wherein the water leaving speed VGWAt 150-200 KM/H.
9. The seaplane takeoff performance verification method as claimed in claim 1, wherein the flight speed VLOFWAt 165-220 KM/H.
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Cited By (2)
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| CN112015109A (en) * | 2020-09-02 | 2020-12-01 | 四川腾盾科技有限公司 | Large unmanned aerial vehicle takeoff and front wheel lift test flight control law and design method thereof |
| CN112380792A (en) * | 2020-11-17 | 2021-02-19 | 中航通飞华南飞机工业有限公司 | Method for evaluating airworthiness conformity of flight performance of amphibious aircraft |
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Effective date of registration: 20221019 Address after: 519040 building 201, 999 Jinhai Middle Road, Jinwan District, Zhuhai City, Guangdong Province Applicant after: SOUTH CHINA AIRCRAFT INDUSTRY CO., LTD. OF CHINA AVIATION INDUSTRY GENERAL AIRCRAFT Co.,Ltd. Address before: 519040 AVIC Tongfei industrial base, aviation industrial park, Jinwan District, Zhuhai City, Guangdong Province Applicant before: R&D INSTITUTE OF CHINA AVIATION INDUSTRY GENERAL AIRCRAFT Co.,Ltd. |
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Application publication date: 20200131 |