Aircraft suspended take-off emergency disposal method based on altitude

Abstract

The invention discloses an altitude-based aircraft takeoff stopping emergency disposal method, which comprises the following steps that: an aircraft accelerates in a takeoff platform, and when a takeoff stopping condition occurs, the aircraft stops accelerating, leaves the takeoff platform and enters a descending stage; in the descending stage, attitude and flight parameters of the aircraft are adjusted, and after adjustment, the aircraft enters the landing stage; in the landing stage, the aircraft enters a plain airport and is braked to dissipate residual kinetic energy, and landing is completed; wherein a descending height difference exists between the take-off platform and the plain airport, and the descending height difference is designed according to flight parameters of an aircraft.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft take-off and landing, and particularly relates to an emergency disposal method for aborting take-off of an aircraft based on altitude. Background Art

[0002] In the design and operation of aerospace vehicles, a core challenge lies in the significant weight changes they face during take-off and landing phases, which are mainly caused by the large amount of fuel required to be carried. This weight difference poses special requirements for the landing gear design of the aircraft. The landing gear must be able to withstand a large weight during landing while maintaining a lightweight structure to avoid affecting the payload capacity and range performance of the aircraft. In traditional designs, in order to reduce the weight of the landing gear, it is usually assumed that the fuel is almost exhausted when the aircraft lands, thereby reducing the landing weight. However, for aerospace vehicles that need to consider emergency aborting take-off during the take-off phase, this conventional design brings significant safety hazards. During the take-off phase, the large amount of fuel carried by the aircraft results in its weight far exceeding the designed landing weight, which not only increases the impact force during landing but also poses higher requirements for the structural strength of the landing gear. Traditional abort take-off methods require the braking device to consume a large amount of energy to stop the aircraft, so the braking system is often designed to be large in size and heavy in weight, greatly affecting other performances of the aircraft. In addition, since emergency landings during the take-off phase usually occur on the runway, the time and space for the aircraft to adjust during landing are very limited, which further increases the difficulty of a safe landing.

[0003] In summary, how to achieve a safe landing for large-weight aerospace vehicles in the case of an urgent need to abort during the take-off phase is an urgent problem to be solved in the prior art. Summary of the Invention

[0004] To solve the above technical problems, the present invention proposes an emergency disposal method for aborting take-off of an aircraft based on altitude, introducing an innovative design concept. This concept should consider the adaptability to the weight changes of the aircraft during take-off and landing phases to ensure a safe landing in case of an emergency while maintaining the performance and efficiency of the aircraft. The present invention involves developing a new landing scheme, improving the design of the braking system, and adopting advanced flight control technologies to achieve dynamic management of weight changes in different flight phases. Through these measures, the safety and reliability of aerospace vehicles during take-off and landing phases can be significantly improved; to solve the problems existing in the above prior art.

[0005] To achieve the above object, the present invention provides an emergency disposal method for aborting take-off of an aircraft based on altitude, including:

[0006] The aircraft accelerates on the take-off platform. When a take-off abort occurs, the aircraft stops accelerating and leaves the take-off platform, entering the descent phase;

[0007] During the descent phase, the attitude and flight parameters of the aircraft are adjusted. After the adjustment, the aircraft enters the landing phase;

[0008] During the landing phase, the aircraft enters a plain airport and brakes to dissipate the remaining kinetic energy to complete the landing;

[0009] There is a descent height difference between the take-off platform and the plain airport, and the descent height difference is designed according to the flight parameters of the aircraft.

[0010] Optionally, the detection process of the occurrence of the take-off abort situation includes:

[0011] Obtain key flight parameters, monitor the key flight parameters. When the monitoring result is abnormal, a take-off abort situation occurs, where the key flight parameters include engine status, aircraft attitude, and speed.

[0012] Optionally, the descent height difference is 2000 meters.

[0013] Optionally, the descent phase includes a flight adjustment phase, a safe flight phase, and a further deceleration phase.

[0014] Optionally, in the flight adjustment phase, the attitude and lift of the aircraft are adjusted to reach a safe flight state.

[0015] Optionally, in the safe flight phase, the safe flight state is maintained.

[0016] Optionally, in the further deceleration phase, the flight attitude, wing angle of attack, and lift of the aircraft are adjusted, and the flight trajectory is optimized to meet the landing requirements.

[0017] Optionally, in the further deceleration phase, it also includes jettisoning fuel from the aircraft and activating a deceleration device to meet the landing requirements.

[0018] Compared with the prior art, the present invention has the following advantages and technical effects:

[0019] 1. Compared with the traditional takeoff and landing solutions of aerospace vehicles, the present invention is particularly optimized for the situation where the aircraft urgently needs to abort takeoff during the takeoff phase, improving flight safety. After the aircraft rushes out of the platform, it will enter the flight state, giving the pilot more time to make emergency decisions, avoiding the urgent situation of having to brake immediately during traditional takeoff, and extending the emergency response time. At the same time, through the "forced landing deceleration mode", the aircraft can not only taxi without power, but also accelerate with the assistance of gravity and reasonably control the speed, avoiding the risks caused by excessive braking;

[0020] 2. Compared with the traditional takeoff and landing solutions of aerospace vehicles, the present invention significantly reduces the burden on the braking system. The traditional way of aborting takeoff requires the braking device to consume a large amount of energy to stop the aircraft, and the braking system is often designed to be bulky and heavy, greatly affecting other performances of the aircraft. In the "forced landing deceleration mode", the aircraft uses the altitude difference for natural descent, reducing the energy dissipation requirement of the braking system, thereby reducing the weight and complexity of the braking device;

[0021] 3. Compared with the traditional takeoff and landing solutions of aerospace vehicles, the present invention optimizes the structural design of the aircraft. Since the deceleration measures taken during the landing process of the aircraft effectively reduce the kinetic energy at landing, there is no longer a need to rely on high-performance and heavy braking devices. This improvement enables the aircraft to adopt a more lightweight design, thereby reducing the weight of the landing gear and enhancing the overall performance and efficiency of the aircraft. At the same time, the heat capacity requirement of the braking system also decreases, which reduces the requirements for the strength and heat resistance of the braking material, further optimizing the design and operating costs of the aircraft.

[0022] 4. Compared with the traditional takeoff and landing solutions of aerospace vehicles, the present invention is more adaptable to complex terrains and has flexibility. This way of aborting takeoff does not rely on a flat ground runway and can be effectively applied in relatively complex or restrictive takeoff environments. Especially under high-altitude or limited space conditions, it provides greater flexibility and safety guarantees. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The drawings constituting a part of this application are used to provide a further understanding of this application. The schematic embodiments of this application and their descriptions are used to explain this application and do not constitute an improper limitation of this application. In the drawings:

[0024] Figure 1 is a schematic flow chart of the method according to an embodiment of the present invention;

[0025] Figure 2 is a schematic diagram of the takeoff phase of the aircraft according to an embodiment of the present invention;

[0026] Figure 3 is a schematic diagram of the flight phase of the aircraft according to an embodiment of the present invention;

[0027] Figure 4 This is a schematic diagram of the landing stage of the aircraft in the embodiment of the present invention. Detailed implementation manners

[0028] It should be noted that, without conflict, the embodiments in the present application and the features in the embodiments may be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and in conjunction with the embodiments.

[0029] It should be noted that the steps shown in the flowchart of the accompanying drawings can be executed in a computer system such as a set of computer-executable instructions, and although the logical order is shown in the flowchart, in some cases, the steps shown or described can be executed in a different order than here.

[0030] The present invention discloses an emergency disposal method for an aircraft to abort takeoff based on altitude. The components and structures involved in the emergency handling method include: aerospace aircraft, highlands, plains, takeoff platforms, plain airports, etc. With the support of the above components and structures, the present invention specifically proposes an emergency disposal method for an aircraft to abort takeoff based on altitude, and this method is designed based on the concept of altitude advantage. The takeoff platform is built or set on a highland with a significant altitude difference, forming a significant drop with the surrounding terrain. During the takeoff stage of the aircraft, once the flight control system detects an abnormality, it will automatically trigger the "forced landing deceleration program". In this emergency program, the aircraft quickly enters a descending trajectory after leaving the takeoff platform. The altitude difference between the highland and the surrounding terrain provides the aircraft with sufficient time and space to adjust its attitude to ensure that the aircraft can smoothly transition to a safe landing state. Subsequently, the aircraft performs a deceleration operation, reducing weight by spraying fuel or other operations to effectively control the descent rate. The flight control system will optimize and adjust the flight trajectory to ensure that the aircraft safely enters the predetermined landing area at an appropriate speed and attitude. During the landing stage, the aircraft will activate the braking system to dissipate the remaining kinetic energy and complete the landing process. Through this design, the present invention provides an efficient and reliable solution for the safe takeoff and emergency disposal of the aircraft.

[0031] The object of the present invention: Aiming at the takeoff and landing requirements of large-weight aerospace aircraft, an emergency disposal method for an aircraft to abort takeoff based on altitude is proposed.

[0032] The main technical problem to be solved by the present invention: How a large-weight aerospace aircraft can land safely when it is necessary to abort during the takeoff stage.

[0033] The present invention discloses the following technical solutions to solve the above problems:

[0034] An emergency disposal method for an aircraft to abort takeoff based on altitude, and the components and structures involved in the emergency disposal method include: aircraft, high ground, plain, takeoff platform, plain airport, etc.

[0035] The takeoff platform is built on or set on the high ground;

[0036] There is a certain height difference between the takeoff platform and the plain airport, and there is a certain horizontal plane distance between a section of the plain airport far from the takeoff platform and the takeoff platform; the height difference is 1000 meters or more, preferably 2000 meters, and the horizontal plane distance is 1000 meters or more, preferably 2000 meters. If reflected in the relationship between the high ground and the plain, the plain is located near the high ground and has a certain left-right height difference, where the left-right height difference is 1000 meters or more, preferably 2000 meters. At the same time, it should be noted that the left-right height difference between the takeoff platform and the plain airport is determined according to the type or performance parameters of the aircraft, and the above values can be determined according to manual experience. At the same time, for the above structure, it can also be determined according to the altitude of the construction location, and the height can meet the height difference required for the above takeoff.

[0037] The lengths of the takeoff platform and the plain airport are constructed according to actual needs. In order to further meet the landing requirements, 3600 meters can be selected.

[0038] The plain airport is built on the plain.

[0039] It should be noted that both the high ground and the plain described above in the present invention belong to a physical structure. The high ground is a flat structure that bears the takeoff platform, and the plain is a flat structure that bears the plain airport, that is, the landing runway. The descriptions of the high ground and the plain are only to distinguish the bearing structures of the two runway platforms with a left-right height difference. The above high ground and plain can be conventionally constructed by means of engineering design and construction on the existing geological structures such as plateaus or mountains, which will not be elaborated here. The takeoff platform and the plain airport are aircraft runway structures and are constructed by the construction method of the runway structure, which will not be elaborated here.

[0040] The present invention also discloses an emergency disposal method for an aircraft to abort takeoff based on altitude, including the following processes:

[0041] The present invention proposes a method for an aircraft to abort takeoff and perform emergency landing relying on natural altitude, and this method is effectively designed based on the principle of altitude advantage. The takeoff platform is located on a high ground with a significant altitude difference, forming a relative drop of about 2000 meters with the surrounding terrain. During the takeoff phase of the aircraft, the flight control system continuously monitors key flight parameters, including but not limited to engine status, aircraft attitude, speed, etc., to ensure flight safety. Once an abnormality in the key flight parameters is detected, the system will automatically evaluate and decide whether to initiate the "crash deceleration procedure". The abnormality of the key flight parameters is detected by judging through conventional status or numerical thresholds.

[0042] After confirming the initiation of the "crash deceleration procedure", the aircraft immediately stops accelerating on the takeoff platform, and the remaining kinetic energy drives the aircraft to leave the takeoff platform set on the high ground and quickly enter the descending trajectory. First, it enters the flight adjustment phase, and the system will automatically adjust the attitude and lift of the aircraft to ensure a smooth transition of the aircraft to a safe flight state. The altitude difference between the high ground and the surrounding terrain provides the necessary time and space for the aircraft, using gravity to increase the descent speed and creating conditions for subsequent deceleration operations. During the safe flight state, the pilot or the automatic control system regulates the descending path of the aircraft to avoid too fast or too slow descent rates. In the safe flight state, it means that the attitude of the aircraft is controlled to a very stable state, the descent rate is slowed down to a relatively slow and stable state, and the aircraft performs a slow landing operation at a stable descent rate at this time. The aircraft only needs to continue to maintain this state and slowly circle to gradually reduce the altitude.

[0043] Among them, when entering the safe flight state, the angle of attack is between -4° and 16°, the sideslip angle is between -4° and 4°, and the speed is between 60 m / s and 280 m / s. After a series of continuous deceleration operations, it is necessary to control the descent rate of the aircraft to about 2 m / s and the landing speed to about 90 m / s before landing.

[0044] When the aircraft enters the safe flight state, it then enters the further deceleration phase. To achieve further deceleration, the aircraft can adjust the flight attitude, change the angle of attack of the wing, increase the lift, etc. When necessary, it can reduce the remaining kinetic energy by timely jettisoning fuel or activating the deceleration device. The flight control system will automatically optimize the flight trajectory based on the real-time feedback data and adjust the flight parameters according to environmental conditions (such as wind speed, air pressure, etc.) to ensure that the aircraft safely enters the predetermined landing area at an appropriate speed and attitude.

[0045] During the landing phase, the aircraft will activate the braking system to dissipate the remaining kinetic energy and complete the landing process. Through this design, the present invention provides an efficient and reliable solution for the safe takeoff and emergency handling of the aircraft, significantly improving the safety and reliability of the aircraft in emergency situations.

[0046] The above technical solution will be described in detail with reference to the relevant drawings:

[0047] The present invention proposes an emergency disposal method for an aircraft aborting takeoff based on altitude. The components and structures involved in the emergency handling method include: aircraft, highlands, plains, takeoff platforms, plain airports, etc.

[0048] As Figure 1 and Figure 2 shown, the takeoff platform is built on the highland, and the end of its runway is designed at the edge of a cliff, such that the takeoff platform has a height difference of approximately 2000 meters relative to the plain. During the takeoff phase, the aerospace vehicle accelerates and taxis on the takeoff platform. During this process, a flight control system equipped with high-precision detection capabilities will monitor key flight parameters in real time, where the flight parameters include but are not limited to engine status, aircraft attitude, speed, etc., to ensure flight safety. By detecting the above flight parameters, once the system detects an anomaly, it will automatically evaluate whether to initiate a "crash landing deceleration procedure". If the aerospace vehicle does not malfunction, or the assessment of the degree of impact of the malfunction is insufficient to trigger the "crash landing deceleration procedure", the aircraft will continue to execute the takeoff action. Conversely, if the system determines that it is necessary to initiate an "emergency crash landing deceleration procedure", the aerospace vehicle will perform an abort takeoff operation on the takeoff platform and use the remaining kinetic energy to taxi away from the takeoff platform and immediately enter a descending trajectory. This process ensures that the aircraft can quickly and safely transition from the takeoff state to the landing preparation state in an emergency.

[0049] As Figure 3 shown, when the aerospace vehicle leaves the takeoff platform, the height difference between the highland and the surrounding terrain provides the necessary time and space for the aircraft to use gravity to increase the descending speed, thereby obtaining sufficient lift to create conditions for subsequent deceleration operations. During this process, the flight control system will precisely regulate the attitude, lift, and descending path of the aircraft, avoiding too fast or too slow descending rates, and ensuring that the aerospace vehicle smoothly transitions to a safe flight state.

[0050] When different faults occur in different aircraft, due to different causes of the faults, the situations formed on the take-off platform are different, and it is necessary to formulate control rules according to different situations. When the aircraft leaves the take-off platform and does not reach a sufficient safe flight speed (the safe flight speed is between 60 m / s and 280 m / s, to avoid being too low and prevent stall), the flight control system automatically controls the aircraft to push the control stick downwards, lower the nose, and at the same time increase the throttle thrust so that the aircraft can obtain sufficient speed to gain lift. After the aircraft obtains sufficient lift, gradually pull the control stick to raise the nose and reduce the throttle thrust to the level flight state. If the aircraft has sufficient speed to gain lift when leaving the high ground, at the appropriate time, directly deflect the elevator upwards to an appropriate angle to make the nose pitch up, control the flap to deploy, and partially deploy the spoiler to increase lift and control the descent rate.

[0051] Among them, the flight control system collects the above information according to the relevant sensing devices set on the aircraft, including a speed sensor and a corresponding attitude sensing device.

[0052] After the aircraft transitions to the safe flight state, in order to achieve further deceleration, the aerospace aircraft can adjust the flight attitude, change the angle of attack of the wing, increase lift, etc. When necessary, it can reduce the remaining kinetic energy by appropriately spraying fuel or activating a deceleration device. The flight control system will automatically optimize the flight trajectory according to the real-time feedback data and adjust the flight parameters according to environmental conditions (such as wind speed, air pressure, etc.) to ensure that the aerospace aircraft safely enters the predetermined landing area at an appropriate speed and attitude.

[0053] In order to achieve further deceleration, during the process of adjusting the flight attitude, changing the angle of attack of the wing, increasing lift, etc., if a smaller descent rate is desired, the elevator of the aircraft is deflected upwards to an appropriate angle to make the nose pitch up, the flap is deployed, and the spoiler is partially deployed to increase lift and control the descent rate. If the adjustment time and space of the aircraft are insufficient, the flight control system can judge whether to consider using a holding pattern, and this subsequent operation will be achieved through the coordinated deflection of the rudder and ailerons.

[0054] During the above process, if the flight control system judges that the descent rate of the aircraft is too large and difficult to adjust to the normal range in time, or detects an abnormal situation with the landing gear of the aircraft, it will appropriately spray fuel or activate a deceleration device to decelerate. During the above process, it is necessary to control the descent rate of the aircraft to be about 2 m / s before landing. The flight control system judges whether this goal can be achieved before touchdown. If it cannot be achieved, the above operations are used to reduce the descent rate.

[0055] In the above process, during the optimization of the flight trajectory, if the adjustment time and space of the aircraft are insufficient, the flight control system can determine whether to consider using hovering to extend the flight path, and this subsequent operation will be achieved through the coordinated deflection of the rudder and ailerons. At the same time, different wind speeds and air pressures will cause different disturbance situations to the aircraft, and the flight control system will automatically adjust the control surfaces to maintain the stability of the flight state (i.e., autopilot in the ordinary sense).

[0056] During the optimization of the flight trajectory, as a supplement to the deceleration process, it is subsequently judged whether the conditions of the descent rate being controlled at about 2 m / s and the landing speed being controlled at about 90 m / s can be met. By means of the above optimization of the flight trajectory, the flight distance is increased and more deceleration operations are performed to meet the above conditions.

[0057] As Figure 4 shown, during the landing phase, the aerospace vehicle will perform a precise landing on the plain airport. At the critical moment when the landing gear contacts the runway, the aerospace vehicle will immediately trigger the braking system to efficiently dissipate its remaining kinetic energy, ensuring that the aerospace vehicle stops on the runway in a safe and stable posture. Before landing, the aircraft effectively reduces the impact force during landing by performing lift augmentation operations and timely fuel dumping and other deceleration measures, thereby reducing the requirement for the design weight of the braking system and optimizing the performance of the overall landing system.

[0058] The above is only a preferred specific embodiment of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed in the present application should be covered by the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. An emergency handling method for aircraft aborted takeoff based on altitude, characterized in that: include: The aircraft accelerates on the take-off platform. When an aborted take-off situation occurs, the aircraft stops accelerating and leaves the take-off platform, entering the descent phase; During the descent phase, the attitude and flight parameters of the aircraft are adjusted, and after the adjustments, the landing phase is entered; During the landing phase, the aircraft enters the plain airport and brakes to dissipate the remaining kinetic energy and complete the landing; There is a descent height difference between the take-off platform and the plain airport, and the descent height difference is designed according to the flight parameters of the aircraft.

2. The method according to claim 1, characterized in that The occurrence detection process of the termination takeoff situation includes: Key flight parameters are obtained and monitored. When the monitoring result is abnormal, the takeoff is aborted. The key flight parameters include engine status, aircraft attitude and speed.

3. The method according to claim 1, characterized in that The descending height difference is 2000 meters.

4. The method according to claim 1, characterized in that The descent phase includes a flight adjustment phase, a safety flight phase and a further deceleration phase.

5. The method according to claim 4, characterized in that During the flight adjustment phase, the attitude and lift of the aircraft are adjusted to achieve a safe flight state.

6. The method according to claim 4, characterized in that During the safe flight phase, the safe flight status is maintained.

7. The method according to claim 4, characterized in that During the further deceleration phase, the aircraft's flight attitude, wing attack angle and lift are adjusted, and the flight trajectory is optimized to meet landing requirements.

8. The method according to claim 1, characterized in that The further deceleration phase also includes spraying fuel on the aircraft and activating the deceleration device to meet landing requirements.

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