CN115924079A - Rapid climbing method for solar aircraft with high aspect ratio - Google Patents
Rapid climbing method for solar aircraft with high aspect ratio Download PDFInfo
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Abstract
The application belongs to the technical field of aviation, and relates to a method for quickly climbing a solar aircraft with a large aspect ratio, wherein a proper carrier aircraft is selected firstly, the solar aircraft is fixed on the carrier through a mounting rack to form an aircraft assembly, an airport, weather and relevant data of the carrier aircraft and the solar aircraft are collected, the aircraft assembly is controlled to roll off and take off until the required speed before climbing is reached, then the rapid climbing route planning of the aircraft is carried out, a climbing speed curve is determined, rapid climbing is realized, the solar aircraft does not need to use a power system of the solar aircraft in the process, a large amount of power of the solar aircraft is saved, the defect of insufficient climbing capacity of the solar aircraft is overcome, the purposes that the solar aircraft can be quickly released and climbs to the target cruising height at any time window are achieved, and after the target airspace and the height are reached, the separation of the carrier aircraft and the solar aircraft is controlled. Greatly reducing climbing time and occupation of airspace, improving safety and being capable of flying and lifting at any time.
Description
Technical Field
The application belongs to the technical field of aviation, and particularly relates to a rapid climbing method for a solar airplane with a large aspect ratio.
Background
The solar aircraft is generally a high-aspect-ratio aircraft with low flying speed, the solar aircraft at home and abroad reaches a preset airspace and a cruising height by adopting a self-climbing method at present, the climbing speed is relatively low, the climbing time is relatively long, and the problem that the airspace is occupied by long-time climbing and the risk of encountering strong gust in the long-time climbing process objectively exist. In addition, since energy consumption is required to be supplemented in real time in the self-climbing process, the solar aircraft is required to fly in the daytime.
Therefore, how to improve the climbing efficiency of the solar airplane and remove or reduce the flying limit of the solar airplane is a problem to be solved.
Disclosure of Invention
The application aims to provide a rapid climbing method for a solar airplane with a large aspect ratio, and the rapid climbing method is used for solving the problems that the existing solar airplane is insufficient in climbing capacity and can only fly off in the daytime.
The technical scheme of the application is as follows: a method for rapidly climbing a solar airplane with a high aspect ratio comprises the following steps:
selecting an airplane meeting the requirements of the technical scheme as a carrying airplane, selecting a proper position by combining the technical characteristics of the carrying airplane and the left and right wings of the solar airplane, additionally installing an installation frame for fixing the solar airplane for the carrying airplane, and modifying a connection mode at the corresponding position of the solar airplane according to a selected separation method;
hoisting the solar airplane to the back of a carrier airplane for fixed connection to form an airplane assembly, and making a route plan of the airplane assembly;
determining the use limit and flight use condition of the airplane assembly, collecting relevant data of an airport, weather, a carrier airplane and a solar airplane, judging whether the current state can meet the requirements of the running takeoff action, and controlling the carrier airplane to execute the running takeoff action until the running takeoff action reaches a set speed if the running takeoff is judged to be possible;
planning a rapid climbing route of the airplane, determining a climbing speed curve, acquiring the current states of the carrier airplane and the solar airplane in real time, judging whether the current states meet the requirement of a rapid climbing action, and if the current states can meet the requirement of the rapid climbing action, executing the rapid climbing action according to the rapid climbing route planning of the airplane;
judging whether the aircraft assembly climbs to a target airspace and height, if so, sending a level flight instruction to the carrier aircraft and the solar aircraft, and adjusting the set flight attitude of the carrier aircraft and the solar aircraft according to the level flight instruction until the carrier aircraft and the solar aircraft reach a stable level flight state;
after the carrier aircraft and the solar aircraft are separated in the air, the carrier aircraft with the mounting frame navigates back, the solar aircraft recovers power and operation, and the mission cruise is started.
Preferably, after the solar aircraft is secured to the carrier aircraft by the mounts, the solar aircraft is held in a negative angle of attack position that produces zero lift.
Preferably, before the carrier aircraft and the solar aircraft fly in a combined manner, a flight line plan of the carrier aircraft and the solar aircraft is made in a ground station, the flight line plan is divided into at least four stages of taking-off, climbing, level flying and air separation, a flying target of each stage is made, during the flight process of the carrier aircraft and the solar aircraft combined manner, the carrier aircraft and the solar aircraft send flight parameters to the ground station at regular intervals, a display interface of the corresponding aircraft parameters is correspondingly arranged on the ground station, the ground station judges the current flight states of the carrier aircraft and the solar aircraft according to the current information, updates the flight line plan of the next stage according to the current flight state, further sends control instructions of the next stage to the carrier aircraft and the solar aircraft, and the carrier aircraft and the solar aircraft adjust the flight speed and the flight attitude according to the control instructions of the current stage.
Preferably, in the combined flight process of the carrier aircraft and the solar aircraft, whether a cloud cluster exists on a route in a certain distance ahead is judged in time, if yes, the ground station changes the current route planning according to the position and the size of the cloud cluster, the size of a path bypassing the cloud cluster and entering the middle of the cloud cluster is judged, and the route with the shortest path is used as the subsequent route planning.
Preferably, the carrier aircraft is a manned or unmanned aircraft; the carrier aircraft is a fuel oil power, fuel-electric hybrid power or electric power aircraft.
Preferably, in the combined flight process of the carrier aircraft and the solar aircraft, the climbing speed of the aircraft assembly is acquired in real time, and whether the climbing speed of the aircraft assembly is less than or equal to the flutter boundary of the solar aircraft is judged; if yes, the aircraft flies normally according to the current route plan; and if not, reducing the climbing speed of the aircraft assembly.
Preferably, the carrier aircraft and the solar aircraft are combined and fixed in a piggyback mode, and the fixed connection point on the mounting rack is arranged at least at one position on the left wing and the right wing of the carrier aircraft.
Preferably, in the combined flight process of the carrier aircraft and the solar aircraft, the flight speed and the axial load of the carrier aircraft are obtained in real time, the relative proportion factor between the flight speed and the axial load is judged, a speed threshold value is set, and when the relative proportion factor is larger than the speed threshold value, the flight speed of the carrier aircraft is reduced; when the relative scaling factor is less than the speed threshold, the flight speed of the carrier aircraft is increased.
Preferably, in the combined flight process of the carrier aircraft and the solar aircraft, the overload of the carrier aircraft is acquired in real time, and when the normal overload of the carrier aircraft is less than 1g, the normal overload of the carrier aircraft is increased; when the normal overload of the carrier aircraft is more than 1g, the normal overload of the carrier aircraft is reduced.
The application provides a method for rapidly climbing a solar aircraft with a large aspect ratio, a proper carrier aircraft is selected firstly, the solar aircraft is fixed on the carrier aircraft through a mounting rack to form an aircraft assembly, relevant data of an airport, weather, the carrier aircraft and the solar aircraft are collected, the aircraft assembly is controlled to roll off and take off until the required speed before climbing is reached, then rapid climbing route planning is carried out on the aircraft, a climbing speed curve is determined, rapid climbing is achieved, the solar aircraft does not need to use a power system of the solar aircraft in the process, a large amount of power of the solar aircraft is saved, the defect of climbing capacity of the solar aircraft is overcome, the purpose that the solar aircraft can be rapidly released and climbed to a target cruising height in any time window is achieved, and the carrier aircraft is controlled to be separated from the solar aircraft after reaching a target airspace and height. Meanwhile, the carrier aircraft can take off at night, so that the climbing time and the occupation of an airspace are greatly reduced, the safety is improved, and the carrier aircraft can fly off at any time.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
FIG. 1 is a schematic diagram of the overall structure of the present application;
fig. 2 is a schematic overall flow chart of the present application.
1. A carrier aircraft; 2. a solar airplane.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
A method for rapidly climbing a solar aircraft with a high aspect ratio, as shown in fig. 1-2, comprises the following steps:
step S100, combined airplane installation and selection
Selecting an airplane meeting the requirements of the technical scheme as a carrier airplane 1, preferably, the carrier airplane 1 can be a manned airplane or an unmanned airplane; meanwhile, the carrier aircraft 1 can be a fuel-powered, oil-electric hybrid power or electric power aircraft.
The carrier aircraft 1 and the solar aircraft 2 perform information interaction with a ground station in real time in the combined flight process, if the carrier aircraft 1 is an unmanned aircraft, the carrier aircraft 1 and the solar aircraft 2 are completely controlled to fly through the ground station, and if the carrier aircraft 1 is a manned aircraft, a pilot determines part of flight control, such as control of the flight speed and the flight attitude.
The technical characteristics of the left wing and the right wing of the carrier aircraft 1 and the solar aircraft 2 are combined, a proper position is selected, the factors of structural arrangement, up-down reverse turning, aerodynamic load on the solar aircraft 2 and the like are considered, a certain position on the left wing and the right wing of the carrier aircraft 1 is generally selected, an installation frame used for fixing the solar aircraft 2 is additionally arranged on the carrier aircraft 1 at the position, and the connection mode is modified according to a selected separation method at the corresponding position of the solar aircraft 2. The connection mode can be selected from axial connection or vertical connection, and the connection mode can adopt a conventional detachable connection mode, such as a screw and the like.
In particular selection, the carrier aircraft 1 preferably has an extension length not less than 40% of the extension length of the solar aircraft 2, and the carrier aircraft 1 preferably has a weight not less than 5 times that of the solar aircraft 2, so as to ensure stability.
Step S200, assembling the combined airplane
Hoisting the solar aircraft 2 to the back of the carrier aircraft 1 for fixed connection, preferably, combining and fixing in a piggyback mode, arranging at least one fixed connection point on the mounting rack on the left wing and the right wing of the carrier aircraft 1, increasing fuselage connection according to situations, forming an aircraft assembly after assembly is finished, and then formulating a course plan of the aircraft assembly;
the mounting bracket should be able to preset a fixed angle of attack for the solar powered aircraft 2 or dynamically adjust the angle of attack of the solar powered aircraft 2. If a preset fixed attack angle is selected, when the aircraft assembly flies flatly, the solar aircraft 2 generates a certain negative attack angle with zero lift force (the angle is determined by the aerodynamic characteristics of the solar aircraft 2 body), so that the wind resistance and the safety are improved.
After the aircraft assembly is assembled, a specific air route plan is formulated according to the characteristics of the combined aircraft assembly, the carrier aircraft 1 is responsible for the power and operation of the aircraft assembly in the processes of takeoff and climbing, and the solar aircraft 2 mainly saves electricity.
The flight line plan is designated in the ground station, the flight line plan is formulated and completed before the run takeoff, the flight line plan is divided into at least four major stages of takeoff, climbing, level flight and air separation, each major stage can be formulated into a plurality of minor stages according to different voyages and/or heights, a flight target of each stage is formulated, after each minor stage in the ground station is completed, the flight data of the current stage is obtained to judge whether the flight target of the stage is completed, and if the flight data of the current stage is completed, the flight plan of the next stage is normally executed; if not, the flight plan of the next stage is adjusted in real time until the flight plan is adjusted to be within the range of the set flight plan.
In the combined flight process of the carrier aircraft 1 and the solar aircraft 2, the carrier aircraft 1 and the solar aircraft 2 send flight parameters to a ground station at regular intervals, a display interface of corresponding aircraft parameters is correspondingly arranged on the ground station, the ground station judges the current flight states of the carrier aircraft 1 and the solar aircraft 2 according to the current information, updates the route plan of the next stage according to the current flight state, further sends a control instruction of the next stage to the carrier aircraft 1 and the solar aircraft 2, and the carrier aircraft 1 and the solar aircraft 2 adjust the flight speed, the flight attitude and the like according to the control instruction of the current stage.
The ground station collects the flight state information of the carrier aircraft 1, and at least comprises a power system, a fuel system, positioning, navigation, attitude and relevant information collection and processing; the solar airplane 2 is only started to position, navigate, acquire and process attitude and related information; the carrier aircraft 1 and the solar aircraft 2 are generally positioned by adopting GPS and Beidou navigation, and other positioning modes can also be adopted.
The ground station mainly carries out information interaction with the flight control systems of the carrier aircraft 1 and the solar aircraft 2, and then transmits interaction information to other systems through the flight control systems.
Step S300, the aircraft assembly runs and takes off
In the flight process, because the solar aircraft 2 is completely exposed above the carrier aircraft 1, the stability of the solar aircraft 2 in the flight process is influenced by aerodynamic characteristics, and therefore the flight speed and the attitude of the aircraft assembly need to be controlled in real time to ensure the flight stability of the aircraft assembly.
Determining the use limit and the flight use condition of the airplane assembly, at least collecting relevant data of an airport, weather, temperature, wind power, a carrier airplane 1 and a solar airplane 2, judging whether the current state can meet the requirements of the roll-off action, and if the roll-off action can be judged, controlling the carrier airplane 1 to execute the roll-off action until a set speed is reached, wherein the set speed is the initial speed required to be reached when the airplane climbs; when the roll-off is carried out, feeding back current flight data to the ground station every time a certain speed is reached, judging whether the current flight state is in the flight route planning range of the current stage by the ground station according to the fed-back information, and if so, continuing the roll-off according to the current flight route plan; if not, correspondingly adjusting the air route plan.
During roll-off and flight, the propeller of the solar powered aircraft 2 may be in a free-spinning windmill state, or may remain stationary.
Step S400, climbing the aircraft assembly
And planning a rapid climbing route of the airplane, determining a climbing speed curve, setting a corresponding aerodynamic model or airplane climbing model at the stage, and simulating the climbing route to determine the most appropriate climbing speed curve so as to realize efficient climbing. The designated completed climb speed profile may be stored in the ground station or in both the carrier aircraft 1 and the solar aircraft 2.
The climbing of the aircraft assembly can be divided into a plurality of stages according to a climbing speed curve, and then real-time control is carried out through data interaction of a ground station, a carrier aircraft 1 and a solar aircraft 2, wherein the specific control method comprises the following steps:
the method comprises the steps of obtaining the current states of a carrier aircraft 1 and a solar aircraft 2 in real time, judging whether the current states meet requirements of rapid climbing actions including speed, posture and the like, if the current states can be judged to be capable of performing the rapid climbing actions, performing the rapid climbing actions according to the rapid climbing route planning of the aircraft, and if a certain stage does not finish a current climbing target, adjusting a current climbing speed curve through a ground station.
Preferably, in the combined flight process of the carrier aircraft 1 and the solar aircraft 2, the climbing speed of the aircraft assembly is acquired in real time, and whether the climbing speed of the aircraft assembly is less than or equal to the flutter boundary of the solar aircraft 2 is judged; if yes, the aircraft flies normally according to the current route plan; if not, the climbing speed of the aircraft assembly is reduced through the ground station entering control, so that the solar flight can be always in a stable flight state in the climbing process.
Preferably, in the combined flight process of the carrier aircraft 1 and the solar aircraft 2, the flight speed and the axial load of the carrier aircraft 1 are obtained in real time, the relative proportion factor between the flight speed and the axial load is judged, a speed threshold value is set, and when the relative proportion factor is larger than the speed threshold value, the flight speed of the carrier aircraft 1 is reduced; when the relative scaling factor is smaller than the speed threshold, the flight speed of the carrier aircraft 1 is increased, and the flight speed of the aircraft combination is slowly changed during the design climb-down process so as to reduce the axial load.
Preferably, in the combined flight process of the carrier aircraft 1 and the solar aircraft 2, the overload of the carrier aircraft 1 is acquired in real time, and when the normal overload of the carrier aircraft 1 is less than 1g, the normal overload of the carrier aircraft 1 is increased; when the normal overload of the carrier aircraft 1 is larger than 1g, the normal overload of the carrier aircraft 1 is reduced, so that the safety of the combination and the solar aircraft 2 is improved, and the flight risk is reduced.
Preferably, in the combined flight process of the carrier aircraft 1 and the solar aircraft 2, whether a cloud cluster exists on a route in a certain distance ahead is judged in time, if yes, the ground station changes the current route planning according to the position and the size of the cloud cluster, the size of a path bypassing the cloud cluster and entering the middle of the cloud cluster is judged, the route with the shortest path is taken as the subsequent route planning, and when the aircraft enters the middle of the cloud cluster, the whole aircraft assembly is ensured to enter the cloud cluster. The situation that the single-side wing passes through the cloud cluster is avoided as much as possible, and the flying risk is reduced.
Preferably, when the carrier aircraft 1 and the solar aircraft 2 fly in combination, a strategy of keeping the sideslip angle of the aircraft within a small range as much as possible should be adopted to reduce the risk.
Meanwhile, if the dangerous area appears on the front air route in the flying process of the airplane assembly, the current air route plan can be changed in a mode of bypassing the dangerous area.
Step S500, the plane assembly flies horizontally
And judging whether the aircraft assembly climbs to a target airspace and height, if so, sending a plane flight instruction to the carrier aircraft 1 and the solar aircraft 2, and adjusting the set flight attitude of the carrier aircraft 1 and the solar aircraft 2 according to the plane flight instruction until the carrier aircraft 1 and the solar aircraft 2 reach a stable plane flight state, wherein the carrier aircraft 1 and the solar aircraft 2 can be separated most stably and efficiently in the plane flight state.
Step S600, separating the airplane assembly
When the set position is reached, the current state information is fed back to a ground station, the ground station judges whether air separation can be executed according to the current information such as height, speed and attitude, if so, an air separation instruction is sent to the carrier aircraft 1 and the solar aircraft 2, the carrier aircraft 1 and the solar aircraft 2 are separated in air through speed difference by controlling the speed and attitude of the carrier aircraft 1 and the solar aircraft 2, for example, the carrier aircraft 1 is separated by a slide rail in an axial speed difference mode, and can be actively far away from the solar aircraft 2 after being completely separated visually; after the carrier aircraft 1 and the solar aircraft 2 are separated in the air, the carrier aircraft 1 returns with the mounting rack for fixing the solar aircraft 2, and the solar aircraft 2 rapidly climbs; the solar aircraft 2 resumes power and maneuvering, starting mission cruise in a clean configuration.
This application is through selecting for use suitable delivery aircraft 1 earlier, fix solar powered aircraft 2 to the delivery through the mounting bracket, form the aircraft assembly, gather the airport, weather, delivery aircraft 1 and solar powered aircraft 2's relevant data, control aircraft assembly roll-off, the required speed before arriving climbing, then carry out the planning of aircraft fast climbing route, confirm the curve of climbing speed, realize fast climbing, solar powered aircraft 2 need not use its driving system at this in-process, a large amount of power of solar powered aircraft 2 has been saved, make up the not enough of solar powered aircraft 2 climbing ability, reach the purpose that arbitrary time window all can be fast released and climb to the height of target cruise, after arriving target airspace and height, control delivery aircraft 1 can with the separation of solar powered aircraft 2. Meanwhile, the carrier aircraft 1 can take off at night, so that the climbing time and the occupation of an airspace are greatly reduced, the safety is improved, and the carrier aircraft can fly off at any time.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (9)
1. A method for rapidly climbing a solar airplane with a high aspect ratio is characterized by comprising the following steps:
selecting an airplane meeting the requirements of the technical scheme as a carrier airplane (1), combining the technical characteristics of the carrier airplane (1) and the left and right wings of the solar airplane (2), selecting a proper position, additionally installing an installation frame for fixing the solar airplane (2) on the carrier airplane (1), and modifying a connection mode according to a selected separation method at a corresponding position of the solar airplane (2);
hoisting the solar airplane (2) to the back of the carrier airplane (1) for fixed connection to form an airplane assembly, and making a route plan of the airplane assembly;
determining the use limit and the flight use condition of the airplane assembly, acquiring relevant data of an airport, weather, a carrier airplane (1) and a solar airplane (2), judging whether the current state can meet the requirements of the running takeoff action, and if the current state can meet the running takeoff action, controlling the carrier airplane (1) to execute the running takeoff action until the running takeoff action reaches a set speed;
planning a rapid climbing route of the airplane, determining a climbing speed curve, acquiring the current states of the carrier airplane (1) and the solar airplane (2) in real time, judging whether the current states meet the requirement of the rapid climbing action, and if the current states can meet the requirement of the rapid climbing action, executing the rapid climbing action according to the rapid climbing route planning of the airplane;
judging whether the aircraft assembly climbs to a target airspace and height, if so, sending a level flight instruction to the carrier aircraft (1) and the solar aircraft (2), and adjusting the set flight attitude of the carrier aircraft (1) and the solar aircraft (2) according to the level flight instruction until the carrier aircraft (1) and the solar aircraft (2) reach a stable level flight state;
when the set position is reached, the carrier aircraft (1) and the solar aircraft (2) are separated in the air, after the carrier aircraft (1) and the solar aircraft (2) are separated in the air, the carrier aircraft (1) carries the mounting frame to return, the solar aircraft (2) recovers power and control, and the mission cruise is started.
2. The method for rapid climb of a high aspect ratio solar powered aircraft as claimed in claim 1, wherein: after the solar aircraft (2) is fixed to the carrier aircraft (1) by means of the mounting frame, the solar aircraft (2) is held in a negative angle of attack position in which zero lift is generated.
3. The method for rapid climb of a high aspect ratio solar powered aircraft as claimed in claim 1, wherein: before the carrier aircraft (1) and the solar aircraft (2) fly in a combined mode, a flight line plan of the carrier aircraft (1) and the solar aircraft (2) is formulated in a ground station, the flight line plan is divided into at least four stages of taking-off, climbing, flat flying and air separation, a flying target of each stage is formulated, in the process of the carrier aircraft (1) and the solar aircraft (2) flying in the combined mode, the carrier aircraft (1) and the solar aircraft (2) transmit flying parameters to the ground station at regular intervals, a display interface of the corresponding aircraft parameters is correspondingly arranged on the ground station, the ground station judges the current flying states of the carrier aircraft (1) and the solar aircraft (2) according to current information, updates the flight line plan of the next stage according to the current flying states, further sends control commands of the next stage to the carrier aircraft (1) and the solar aircraft (2), and the carrier aircraft (1) and the solar aircraft (2) adjust flying speed and flying attitude according to the control commands of the current stage.
4. The method for rapid climb of a high aspect ratio solar powered aircraft according to claim 3, characterized in that: in the combined flight process of the carrier aircraft (1) and the solar aircraft (2), whether a cloud cluster exists on a route in a certain distance ahead is judged in time, if yes, the ground station changes the current route planning according to the position and the size of the cloud cluster, the size of a path bypassing the cloud cluster and entering the middle of the cloud cluster is judged, and the route with the shortest path is used as the subsequent route planning.
5. The method for rapid climb of a high aspect ratio solar powered aircraft as claimed in claim 1, wherein: the carrier aircraft (1) is a manned or unmanned aircraft; the carrier aircraft (1) is a fuel oil power, fuel-electric hybrid power or electric power aircraft.
6. The method for rapid climb of a high aspect ratio solar powered aircraft as claimed in claim 1, wherein: in the combined flight process of the carrier aircraft (1) and the solar aircraft (2), acquiring the climbing speed of the aircraft assembly in real time, and judging whether the climbing speed of the aircraft assembly is less than or equal to the flutter boundary of the solar aircraft (2); if yes, the aircraft flies normally according to the current route plan; and if not, reducing the climbing speed of the aircraft assembly.
7. The method for rapid climb of a high aspect ratio solar powered aircraft as claimed in claim 1, wherein: the carrier aircraft (1) and the solar aircraft (2) are combined and fixed in a piggyback mode, and at least one fixed connection point on the mounting rack is arranged on the left wing and the right wing of the carrier aircraft (1).
8. The method for rapid climb of a high aspect ratio solar powered aircraft as claimed in claim 1, wherein: in the combined flight process of the carrier aircraft (1) and the solar aircraft (2), acquiring the flight speed and the axial load of the carrier aircraft (1) in real time, judging the relative proportion factor between the flight speed and the axial load, setting a speed threshold, and reducing the flight speed of the carrier aircraft (1) when the relative proportion factor is greater than the speed threshold; when the relative scaling factor is less than the speed threshold, the flying speed of the carrier aircraft (1) is increased.
9. The method for rapid climb of a high aspect ratio solar powered aircraft as claimed in claim 1, wherein: in the combined flight process of the carrier aircraft (1) and the solar aircraft (2), the overload of the carrier aircraft (1) is acquired in real time, and when the normal overload of the carrier aircraft (1) is less than 1g, the normal overload of the carrier aircraft (1) is increased; when the normal overload of the carrying aircraft (1) is larger than 1g, the normal overload of the carrying aircraft (1) is reduced.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202211617127.9A CN115924079A (en) | 2022-12-15 | 2022-12-15 | Rapid climbing method for solar aircraft with high aspect ratio |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211617127.9A CN115924079A (en) | 2022-12-15 | 2022-12-15 | Rapid climbing method for solar aircraft with high aspect ratio |
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| CN115924079A true CN115924079A (en) | 2023-04-07 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116611175A (en) * | 2023-07-18 | 2023-08-18 | 北京航空航天大学 | Prediction method for free degree flutter of large aspect ratio aircraft body |
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2022
- 2022-12-15 CN CN202211617127.9A patent/CN115924079A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116611175A (en) * | 2023-07-18 | 2023-08-18 | 北京航空航天大学 | Prediction method for free degree flutter of large aspect ratio aircraft body |
| CN116611175B (en) * | 2023-07-18 | 2023-09-12 | 北京航空航天大学 | Prediction method for free degree flutter of large aspect ratio aircraft body |
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