阅读说明：本技术 智能任务热管理系统 (Intelligent task thermal management system ) 是由 亨德里克·皮耶特·雅各布斯·德·博克 马修·罗伯特·塞尔尼 加里·夸肯布什 埃里克·韦斯特维尔 于 2019-08-01 设计创作，主要内容包括：根据一些实施例,提供了一种系统和方法,包括：在任务执行模块处接收飞行器任务的一个或多个任务目标,以及条件数据；经由任务执行模块生成任务计划,任务计划能够执行以经由操纵动力热管理系统(PTMS)来解决一个或多个任务目标中的至少一个任务目标；在PTMS处,直接从任务执行模块接收在PTMS处生成的所述任务计划；以及自动执行生成的任务计划以操作飞行器。提供了许多其他方面。(According to some embodiments, there is provided a system and method comprising: receiving, at a task execution module, one or more task targets for an aircraft task, and condition data; generating, via a task execution module, a task plan executable to address at least one task objective of the one or more task objectives via a maneuver-Powered Thermal Management System (PTMS); receiving, at the PTMS, the task plan generated at the PTMS directly from a task execution module; and automatically executing the generated mission plan to operate the aircraft. Numerous other aspects are provided.)

1. A method, comprising:

receiving, at a task execution module, one or more task targets and condition data for an aircraft task;

generating, via the task execution module, a mission plan executable to address at least one of the one or more mission objectives via a maneuver-Powered Thermal Management System (PTMS);

receiving, at the PTMS, the generated task plan directly from the task execution module; and

automatically executing the generated mission plan to operate an aircraft.

2. The method of claim 1, further comprising:

determining a change in at least one of: one or more task objectives and the condition data;

generating, via the task execution module, an additional mission plan based on the change in at least one of the one or more mission goals and the condition data; and

executing the generated additional mission plan to operate the aircraft.

3. The method of claim 1, wherein the mission plan generated is based on data provided by a digital twin model.

4. The method of claim 3, further comprising:

detecting fault data with one or more subsystems of the PTMS and updating the digital twin with the detected fault data.

5. The method of claim 1, wherein receiving condition data further comprises at least one of:

receiving or determining weather information;

receiving an engine state;

receiving a propulsion system state;

receiving a flight surface condition; and

a power thermal management state is received.

6. The method of claim 5, wherein the engine state comprises at least one of a temperature, a fuel flow, a speed, and an efficiency of at least one engine, the propulsion system state comprises a fuel temperature, a power distribution between a motor and a turbine, a fuel gauge indicating a fuel level, the flight surface state comprises flight surface damage/effectiveness, and the power thermal management state comprises at least one of a radiator temperature, a fuel flow rate and temperature, a coolant flow rate and temperature, and a thermal energy storage state and temperature.

7. The method of claim 5, wherein at least one of the weather information, engine status, propulsion system status, flight surface status, and power thermal management status is estimated.

8. The method of claim 1, wherein the one or more task goals are at least one of: reduced fuel consumption, increased flight range, and increased electrical and heat sink capacity for high power systems.

9. The method of claim 1, wherein the execution of the mission plan further comprises:

modifying the operation of at least one subsystem of the PTMS via an operation input.

10. A system, comprising:

a task execution module that receives one or more task goals for an aircraft task, and condition data;

a memory for storing program instructions;

a task processor coupled to the memory and in communication with the task execution module and operable to execute program instructions to:

generating a mission plan executable to address at least one of the one or more mission objectives via a maneuver-Powered Thermal Management System (PTMS);

receiving, at the PTMS, the generated task plan directly from the task execution module; and

automatically executing the generated mission plan to operate the aircraft.

Technical Field

The invention relates to an intelligent task thermal management system.

Background

For commercial and military aircraft, there is a move toward electrified aircraft (MEA). The MEA trend describes a rapid increase in demand for on-board power (countermeasure, avionics, interference, directed energy weapons, etc.). For military aircraft, the benefits of MEAs not only serve to increase range, but may also translate into increased capacity. A Power Thermal Management System (PTMS) may be used to address thermal loading of various aircraft systems. As the demand for onboard power increases, it may become increasingly difficult to manage the tradeoffs that exist between the different goals of PTMS.

It is desirable to provide systems and methods that improve the operation of PTMS to optimize the operational control of PTMS.

Disclosure of Invention

According to some embodiments, a method comprises: receiving, at a task execution module, one or more task targets and condition data for an aircraft task; generating, via a task execution module, a task plan executable to address at least one task objective of the one or more task objectives via a maneuver-Powered Thermal Management System (PTMS); receiving, at the PTMS, the generated task plan directly from the task execution module; and automatically executing the generated mission plan to operate the aircraft.

According to some embodiments, a system comprises: a task execution module that receives one or more task objectives for an aircraft task, and condition data; a memory for storing program instructions; a task processor coupled to the memory and in communication with the task execution module and operable to execute the program instructions to: generating a mission plan executable to address at least one of the one or more mission objectives via a maneuver-Powered Thermal Management System (PTMS); receiving the generated task plan directly from the task execution module at the PTMS; and automatically executing the generated mission plan to operate the aircraft.

According to some embodiments, a non-transitory computer-readable medium storing instructions that, when executed by a computer processor, cause the computer processor to perform a method comprising: receiving, at a task execution module, one or more task targets for an aircraft task; generating, via a task execution module, a task plan executable to address at least one task objective of the one or more task objectives via a maneuver-Powered Thermal Management System (PTMS); receiving the generated task plan directly from the task execution module at the PTMS; and automatically executing the generated mission plan to operate the aircraft.

A technical effect of some embodiments of the present invention is an improved and/or computerized technique and system for a mission execution plan director and a mission execution module for an aircraft having a Power Thermal Management System (PTMS). Embodiments provide PTMS architectures that can take into account available radiators (including fuel, ram air, and engine secondary flow streams) to effectively manage increased aircraft thermal loads for anticipated next generation aircraft demands. The inventors have noted that potential next generation thermal load increases may be a result of mission critical system capabilities, advanced Directed Energy Weapon (DEW) systems and larger electrified aircraft engine accessories (e.g., generators) driving enhanced mission capabilities. Embodiments provide optimization of the relationship between vehicle load and radiator provided by a variable cycle engine. Embodiments provide optimization via integration of an adaptive subsystem that provides the thermal lift required to maximize heat sink utilization in the most efficient manner. Embodiments provide a power source (e.g., an engine bleed air, electric power, or standalone TMS combustor) for "thermal lift" (e.g., to make thermal energy "hot enough" to be expelled in a hotter environment). In an embodiment, the thermal lift may be a system objective/constraint. Embodiments provide for work distribution between the engine (if multiple engines), spools (high and low pressure) and thermal lift options (e.g., VCS and ACM), smaller high and low pressure generators for mixed bleed air, and multiple Environmental Control System (ECS) packs.

Future aircraft are expected to use advanced integrated propulsion-power-thermal management systems (IPPTMS), which is an improvement over PTMS or basic Flight Management System (FMS) avionics in use today. For example, embodiments provide IPPTMS operation under the direction of a task direction module and a task execution module that manages tradeoffs between survivability, capacity, scope, and heat sink availability. With respect to cooling fuel (or other thermal storage), for example, the task direction module and task execution module may manage the tradeoff of immediate cooling fuel in anticipation of future demand, at the expense of increased immediate fuel consumption. As a more specific example, the trade-off may be that more heat storage is now created and flown over a more threatening environment, or that fuel is now saved and a longer path is flown around the environment. Embodiments may provide task options (e.g., where to fly and how to fly) via a task guidance module to achieve additional tradeoffs.

Drawings

FIG. 1 illustrates a system according to some embodiments.

Fig. 2A illustrates a system diagram according to some embodiments.

Fig. 2B illustrates a system diagram according to some embodiments.

FIG. 3 illustrates a flow diagram according to some embodiments.

FIG. 4 illustrates a map according to some embodiments.

FIG. 5 illustrates a user interface according to some embodiments.

Fig. 6A illustrates a system diagram according to some embodiments.

Fig. 6B illustrates a system diagram according to some embodiments.

FIG. 7 illustrates a flow diagram according to some embodiments.

FIG. 8 illustrates a block diagram of a system according to some embodiments.

FIG. 9 illustrates a table according to some embodiments.

Embodiments may manage the tradeoffs internally via the task execution module and self-select an optimized task based on one or more rules, and then automatically provide the selected task as input to one or more subsystems to execute the task. For example, embodiments provide coupling of aircraft subsystems to achieve optimal task performance. The strategy may include modifying adaptive subsystem characteristics such as allocation between low and high linear axis power extraction, priority of heat sink usage, and other aspects of achieving optimized results. Embodiments may also provide, in contrast to conventional approaches: improved combat damage tolerance to better withstand damage to certain aspects of an asset before the asset is unable to perform an action (e.g., if a first thermal management device is disabled, a second thermal management device with similar functionality may compensate for the loss due to the first thermal management device); adaptive PTMS adjustment and function control, where other systems may get slack (slack) from the missing functions of other components, so that the system is not just out of service; intelligent fault isolation and mitigation; and energy compatible selective heat sink utilization in response to aircraft commands and controls.

It should be noted that the difference between the mission guidance module and the mission execution module is that the mission guidance module generates several mission plan options for the pilot or system to select and then execute, while the mission execution module generates a single mission plan that is automatically executed by the system when it generates. It should also be noted that a benefit of the task execution module is that the system does not need to rely on communications to determine actions, which can provide enhanced security, as no communications, execution of a task plan can avoid interception.

With this and other advantages and features, which will become apparent below, a more complete understanding of the nature of the present invention may be obtained by reference to the following detailed description and to the accompanying drawings.

Other embodiments are associated with systems and/or computer-readable media that store instructions to perform any of the methods described herein.