A high-mach vehicle power system

Abstract

The application belongs to the technical field of high Mach number aircraft power system design, and particularly relates to a high Mach number aircraft power system, on the basis of a Mach number two aircraft power system, an APU+EPU scheme is adopted for the auxiliary power system, and a ram turbine is additionally arranged, the auxiliary power system can be used as an emergency energy source when the flight speed exceeds 2 Mach, main engine in-flight accidental shutdown and other abnormal conditions occur, so as to ensure the flight safety of the aircraft, in addition, the auxiliary power system can provide reliable auxiliary energy for the aircraft during aircraft mode conversion and in-flight unpowered taxiing, so as to keep the energy supply stable and ensure the continuous and reliable operation of the aircraft.

Description

Technical Field

[0001] This application belongs to the field of high Mach number aircraft propulsion system design technology, specifically relating to a high Mach number aircraft propulsion system. Background Technology

[0002] An auxiliary power system is installed in the aircraft's power system to provide auxiliary power to the aircraft during ground static states such as ground inspections and ground standby, as well as in the event of an unexpected in-flight engine failure, ensuring the aircraft's operation and safety.

[0003] Mach 2 level aircraft propulsion system such as Figure 1 As shown, it mainly includes an auxiliary power system and a main engine. The auxiliary power system adopts an APU solution and operates as follows under various conditions:

[0004] When the aircraft is stationary on the ground, the main engines are off, and the auxiliary power system is working. The auxiliary power system provides compressed air to the aircraft's air system, electrical energy to the aircraft's energy system, and hydraulic pressure to the aircraft's hydraulic system.

[0005] When the main engine is started on the ground, the auxiliary power system works. The APU in the auxiliary power system provides starting air to the starter, which rotates the starter and drives the main engine through the aircraft accessory gearbox and engine transmission system, thus starting the main engine.

[0006] When in flight, at speeds below Mach 2, the main engine operates while the auxiliary power system shuts down. The main engine drives the main generator and main hydraulic pump through the engine transmission system and aircraft accessory gearbox. The main generator provides electrical power to the aircraft's energy system, and the main hydraulic pump provides hydraulic pressure to the aircraft's hydraulic system, while simultaneously providing compressed air to the aircraft's air system.

[0007] When the main engine fails unexpectedly in flight, and the flight altitude is below 10 km and the flight speed is below Mach 1, the auxiliary power system (APU) will activate. The APU in the APU provides starting air to the starter motor, causing the starter motor to rotate. This rotation drives the main engine through the aircraft accessory gearbox and engine transmission system, thus starting the main engine. At the same time, the APU provides compressed air to the aircraft's air system, electrical energy to the aircraft's energy system, and hydraulic pressure to the aircraft's hydraulic system, ensuring that the aircraft can operate normally in the air and ensuring the aircraft's flight safety.

[0008] At present, the power system of a Mach 2 aircraft is used as the power system of a high Mach number aircraft. However, the maximum flight envelope of the high Mach number aircraft exceeds that of the Mach 2 aircraft. When the flight speed exceeds 2 Mach, the auxiliary power system cannot work normally, and cannot provide emergency energy when the main engine is unexpectedly stopped in the air or other abnormal conditions occur, so that the flight safety of the aircraft is difficult to guarantee. In addition, the high Mach number aircraft has special scenarios that the Mach 2 aircraft does not encounter, such as air mode conversion and air unpowered sliding. In such scenarios, the main engine cannot provide continuous and sufficient energy for the aircraft, and it is difficult to meet the needs of the aircraft operation.

[0009] The present application is proposed in view of the existence of the above technical defects.

[0010] It should be noted that the disclosure of the above background art is only used to assist in understanding the inventive concept and technical solutions of the present application, and does not necessarily belong to the prior art of the present application. In the absence of explicit evidence that the above content has been disclosed on the filing date of the present application, the above background art should not be used to evaluate the novelty and inventiveness of the present application. SUMMARY

[0011] The purpose of the present application is to provide a high Mach number aircraft power system to overcome or alleviate at least one aspect of the known technical defects.

[0012] The technical solution of the present application is:

[0013] A high Mach number aircraft power system, comprising a main engine, an auxiliary power system and a ram turbine, wherein:

[0014] The main engine is connected to the aircraft accessory gearbox through an engine transmission system, and the aircraft accessory gearbox is connected to a main generator and a main hydraulic pump, wherein the main generator is connected to an aircraft energy system, and the main hydraulic pump is connected to an aircraft hydraulic system;

[0015] The auxiliary power system adopts an APU+EPU scheme and is connected to an aircraft air system, an aircraft energy system, an aircraft hydraulic system and a starter, wherein the starter is connected to the aircraft accessory gearbox;

[0016] The ram turbine is connected to an aircraft runway and is connected to the aircraft accessory gearbox through a clutch.

[0017] In the ground static state, the main engine is stopped, the ram turbine is stopped, the clutch is disconnected, and the auxiliary power system works, and the auxiliary power system provides compressed air to the aircraft air system, provides electric energy to the aircraft energy system, and provides hydraulic pressure to the aircraft hydraulic system;

[0018] When the main engine is started on the ground, the ram turbine is stopped, the clutch is disconnected, and the auxiliary power system works. The APU in the auxiliary power system provides starting air to the starter, so that the starter rotates. The starter drives the main engine through the aircraft accessory gearbox and the engine transmission system, so that the main engine starts;

[0019] When the aircraft flies at low speed in the air, the ram turbine is stopped, the clutch is disconnected, and the auxiliary system is stopped. The main engine drives the main generator and the main hydraulic pump through the engine transmission system and the aircraft accessory gearbox. The main generator provides electric energy to the aircraft energy system, and the main hydraulic pump provides hydraulic pressure to the aircraft hydraulic system.

[0020] When the main engine is unexpectedly stopped in the air, the ram turbine is stopped, the clutch is disconnected, and the auxiliary power system works. The EPU in the auxiliary power system provides starting air to the starter, so that the starter rotates. The starter drives the main engine through the aircraft accessory gearbox and the engine transmission system, so that the main engine starts. At the same time, the auxiliary power system provides compressed air to the aircraft air system, provides electric energy to the aircraft energy system, and provides hydraulic pressure to the aircraft hydraulic system.

[0021] When the aircraft is unpowered in the air, the main engine is stopped, the ram turbine works, the clutch is connected, and the auxiliary power system works. The aircraft inlet introduces high-temperature and high-pressure air to the ram turbine, which drives the ram turbine to work. The ram turbine drives the aircraft accessory gearbox through the clutch, and then drives the main generator and the main hydraulic pump. The main generator provides electric energy to the aircraft energy system, and the main hydraulic pump provides hydraulic pressure to the aircraft hydraulic system. At the same time, the EPU in the auxiliary power system provides compressed air to the aircraft air system, provides electric energy to the aircraft energy system, and provides hydraulic pressure to the aircraft hydraulic system.

[0022] When the aircraft is in a mode conversion in the air, the main engine gradually changes from working to stopping, the ram turbine gradually changes from stopping to high working state, the clutch is connected, and the auxiliary power system works. The EPU in the auxiliary power system provides compressed air to the aircraft air system, provides electric energy to the aircraft energy system, and provides hydraulic pressure to the aircraft hydraulic system.

[0023] When the aircraft flies at high speed in the air, the main engine is stopped, the ram turbine works, the clutch is connected, and the auxiliary system is stopped. The aircraft inlet introduces high-temperature and high-pressure air to the ram turbine, which drives the ram turbine to work. The ram turbine drives the aircraft accessory gearbox through the clutch, and then drives the main generator and the main hydraulic pump. The main generator provides electric energy to the aircraft energy system, and the main hydraulic pump provides hydraulic pressure to the aircraft hydraulic system.

[0024] According to at least one embodiment of the present application, in the above-mentioned high-Mach-number aircraft power system, when the aircraft flies at low speed in the air, the flight speed is less than 2 Mach;

[0025] When the aircraft is unpowered in the air, the flight speed is less than 3 Mach and greater than 2 Mach.

[0026] The flight speed is less than 3 Mach and greater than 2 Mach when the aircraft is in the air mode conversion;

[0027] The flight speed is less than 5 Mach and greater than 3 Mach when the aircraft is in the high-speed flight in the air. BRIEF DESCRIPTION OF DRAWINGS

[0028] Figure 1 is a schematic diagram of a Mach number two aircraft power system provided by an embodiment of the present application;

[0029] Figure 2 is a schematic diagram of a high Mach number aircraft power system provided by an embodiment of the present application.

[0030] In order to better illustrate the embodiments, some components in the drawings may be omitted, enlarged or reduced, and do not represent the actual size of the product. In addition, the drawings are only used for illustrative description and cannot be understood as a limitation of the present application. DETAILED DESCRIPTION

[0031] In order to make the technical solutions of the present application and its advantages clearer, the technical solutions of the present application will be further clearly and completely described below with reference to the drawings. It should be understood that the specific embodiments described herein are only part of the embodiments of the present application, and are only used to explain the present application, but not to limit the present application. It should be noted that, in order to facilitate the description, only parts related to the present application are shown in the drawings, and other related parts can be referred to the usual design. In the case of no conflict, the embodiments in the present application and the technical features in the embodiments can be combined to obtain new embodiments.

[0032] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer," etc., used in this application description to indicate relative direction or positional relationship are used only to indicate relative orientation or positional relationship, and do not imply that the device or component must have a specific orientation, or be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, and therefore should not be construed as a limitation on this application. The terms "first," "second," "third," and similar terms used in this application description are used only for descriptive purposes to distinguish different components, and should not be construed as indicating or implying relative importance. The terms "a," "one," or "the," etc., used in this application description should not be construed as an absolute limitation on quantity, but should be construed as indicating the existence of at least one. The terms "including," "comprising," etc., used in this application description mean that the element or object preceding the word covers the element or object listed after the word and its equivalents, without excluding other elements or objects.

[0033] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as “installation,” “connection,” and “linkage” used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; or it can be a connection within two components. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0034] The following is in conjunction with the appendix Figures 1 to 2 This application will be described in further detail.

[0035] A high Mach number aircraft propulsion system includes a main engine, an auxiliary power system, and a ramjet turbine, wherein:

[0036] The main engine is connected to the aircraft accessory housing via the engine transmission system. The main generator and the main hydraulic pump are connected to the aircraft accessory housing. The main generator is connected to the aircraft energy system, and the main hydraulic pump is connected to the aircraft hydraulic system.

[0037] The auxiliary power system adopts the APU+EPU scheme, which connects the aircraft air system, aircraft energy system, aircraft hydraulic system, and starter. The starter is connected to the aircraft accessory housing. The APU is the Auxiliary Power Unit, and the EPU is the Emergency Power Unit.

[0038] The ram turbine is connected to the aircraft inlet duct and to the aircraft accessory gearbox through a clutch.

[0039] The high Mach number aircraft power system provided by the present application works as follows in various situations:

[0040] In the ground static state, the main engine is stopped, the ram turbine is stopped, the clutch is disconnected, and the auxiliary power system works, the auxiliary power system provides compressed air to the aircraft air system, provides electric energy to the aircraft energy system, and provides hydraulic pressure to the aircraft hydraulic system;

[0041] When the main engine is started on the ground, the ram turbine is stopped, the clutch is disconnected, and the auxiliary power system works, the APU in the auxiliary power system provides starting air to the starter to make the starter rotate, and the main engine is started by the aircraft accessory gearbox and the engine transmission system;

[0042] When flying at low speed in the air, the flight speed is less than 2 Mach, the main engine works, the ram turbine is stopped, the clutch is disconnected, and the auxiliary system is stopped, the main engine drives the main generator and the main hydraulic pump through the engine transmission system and the aircraft accessory gearbox, the main generator provides electric energy to the aircraft energy system, the main hydraulic pump provides hydraulic pressure to the aircraft hydraulic system, and compressed air is provided to the aircraft air system at the same time;

[0043] When the main engine is unexpectedly stopped in the air, the ram turbine is stopped, the clutch is disconnected, and the auxiliary power system works, the EPU in the auxiliary power system provides starting air to the starter to make the starter rotate, and the main engine is started by the aircraft accessory gearbox and the engine transmission system, at the same time, the auxiliary power system provides compressed air to the aircraft air system, provides electric energy to the aircraft energy system, and provides hydraulic pressure to the aircraft hydraulic system, to ensure that the aircraft can operate normally in the air and ensure the flight safety of the aircraft;

[0044] When unpowered taxiing in the air, the flight speed is less than 3 Mach and greater than 2 Mach, the main engine is stopped, the ram turbine works, the clutch is connected, and the auxiliary power system works, the aircraft inlet duct introduces high-temperature and high-pressure air to the ram turbine to drive the ram turbine to work, the ram turbine drives the aircraft accessory gearbox through the clutch, and then drives the main generator and the main hydraulic pump, the main generator provides electric energy to the aircraft energy system, and the main hydraulic pump provides hydraulic pressure to the aircraft hydraulic system, at the same time, the EPU in the auxiliary power system provides compressed air to the aircraft air system, provides electric energy to the aircraft energy system, and provides hydraulic pressure to the aircraft hydraulic system, to make up for the fact that the ram turbine cannot provide sufficient energy to the aircraft at a lower aircraft speed, and to ensure that the aircraft can work continuously and reliably;

[0045] When the air mode is converted, the flight speed is less than 3 Mach and greater than 2 Mach, the main engine is gradually changed from working to stopping, the ram turbine is gradually changed from stopping to high working state, the clutch is connected, and the auxiliary power system works, the EPU in the auxiliary power system provides compressed air to the aircraft air system, provides electric energy to the aircraft energy system, and provides hydraulic pressure to the aircraft hydraulic system, so as to make up for the fact that the main engine and the ram turbine cannot provide sufficient energy to the aircraft during the process, and ensure that the aircraft can work continuously and reliably.

[0046] When the aircraft flies at high speed in the air, the flight speed is less than 5 Mach and greater than 3 Mach, the main engine is stopped, the ram turbine works, the clutch is connected, and the auxiliary system is stopped, the aircraft inlet duct introduces high-temperature and high-pressure air to the ram turbine to drive the ram turbine to work, the ram turbine drives the aircraft accessory case through the clutch, and then drives the main generator and the main hydraulic pump to provide electric energy to the aircraft energy system through the main generator and provide hydraulic pressure to the aircraft hydraulic system through the main hydraulic pump, and at the same time, compressed air is provided to the aircraft air system, so that the ram turbine can provide sufficient energy to the aircraft at a higher flight speed, and ensure that the aircraft can work continuously and reliably.

[0047] The high-Mach-number aircraft power system disclosed in the above embodiments, in which the main engine, the auxiliary power system, the ram turbine and the clutch thereof can be connected to the flight control system, and the working state of the main engine, the auxiliary power system, the ram turbine and the clutch thereof is controlled by the flight control system.

[0048] The high-Mach-number aircraft power system disclosed in the above embodiments, based on the Mach number two-level aircraft power system, designs the auxiliary power system to adopt the APU+EPU scheme, and adds a ram turbine, so that the auxiliary power system can provide emergency energy when the flight speed exceeds 2 Mach and the main engine is unexpectedly stopped in the air or other abnormal conditions, to ensure the flight safety of the aircraft, and in addition, the auxiliary power system can provide reliable auxiliary energy for the aircraft during the mode conversion of the aircraft and the air unpowered taxiing process, to keep the energy supply stable and ensure the continuous and reliable operation of the aircraft.

[0049] The embodiments in the specification are described in a progressive manner, and each embodiment focuses on the difference from other embodiments. The same or similar parts of each embodiment can be referred to each other.

[0050] So far, the technical solution of the application has been described in combination with the preferred embodiments shown in the drawings. It should be understood by those skilled in the art that the protection scope of the application is obviously not limited to these specific embodiments. Without deviating from the principles of the application, those skilled in the art can make equivalent changes or replacements to the related technical features, and the technical solutions after the changes or replacements will fall within the protection scope of the application.

Claims

1. A high Mach number aircraft propulsion system, characterized in that, Includes the main engine, auxiliary power system, and ramjet turbine, among which: The main engine is connected to the aircraft accessory housing via the engine transmission system. The main generator and the main hydraulic pump are connected to the aircraft accessory housing. The main generator is connected to the aircraft energy system, and the main hydraulic pump is connected to the aircraft hydraulic system. The auxiliary power system adopts the APU+EPU scheme, which connects the aircraft air system, aircraft energy system, aircraft hydraulic system, and starter. The starter is connected to the aircraft accessory housing. The ram turbine is connected to the aircraft's feed path and to the aircraft's accessory housing via a clutch; When the aircraft is stationary on the ground, the main engine stops, the ramjet turbine stops, the clutch disengages, and the auxiliary power system operates. The auxiliary power system supplies compressed air to the aircraft's air system, electrical energy to the aircraft's energy system, and hydraulic pressure to the aircraft's hydraulic system. When the main engine is started on the ground, the ramjet turbine stops, the clutch disengages, and the auxiliary power system (APU) starts working. The APU in the APU supplies starting air to the starter motor, causing the starter motor to rotate. This rotation drives the main engine through the aircraft accessory housing and the engine transmission system, thus starting the main engine. When flying at low speeds in the air, the main engine is running, the ramjet turbine is shut down, the clutch is disengaged, the auxiliary systems are shut down, and the main engine drives the main generator and the main hydraulic pump through the engine transmission system and the aircraft accessory gearbox. The main generator provides electrical energy to the aircraft energy system, and the main hydraulic pump provides hydraulic pressure to the aircraft hydraulic system. When the main engine fails unexpectedly in the air, the ramjet turbine stops, the clutch disengages, and the auxiliary power system (EPU) starts working. The EPU in the APU supplies starting air to the starter, causing the starter to rotate. This rotation drives the main engine through the aircraft accessory housing and engine transmission system, thus starting the main engine. At the same time, the APU supplies compressed air to the aircraft air system, electrical energy to the aircraft energy system, and hydraulic pressure to the aircraft hydraulic system. When the aircraft is taxiing without power, the main engine shuts down, the ramjet turbine operates, the clutch engages, and the auxiliary power system operates. The aircraft's air intake introduces high-temperature, high-pressure air into the ramjet turbine, driving it to do work. The ramjet turbine, through the clutch, drives the aircraft accessory gearbox, which in turn drives the main generator and the main hydraulic pump. The main generator provides electrical power to the aircraft's energy system, and the main hydraulic pump provides hydraulic power to the aircraft's hydraulic system. At the same time, the EPU in the auxiliary power system provides compressed air to the aircraft's air system, electrical power to the aircraft's energy system, and hydraulic power to the aircraft's hydraulic system. During the in-flight mode transition, the main engine gradually transitions from operating to shutting down, the ramjet turbine gradually transitions from shutting down to high operating status, the clutch engages, the auxiliary power system operates, and the EPU in the auxiliary power system provides compressed air to the aircraft air system, electrical energy to the aircraft energy system, and hydraulic pressure to the aircraft hydraulic system. When flying at high speed in the air, the main engine stops, the ramjet turbine works, the clutch engages, the auxiliary system stops, the aircraft air intake introduces high temperature and high pressure air into the ramjet turbine, driving the ramjet turbine to do work. The ramjet turbine drives the aircraft accessory housing through the clutch, which in turn drives the main generator and the main hydraulic pump. The main generator provides electrical energy to the aircraft energy system, and the main hydraulic pump provides hydraulic pressure to the aircraft hydraulic system. When an aircraft is flying at low speed in the air, its speed is below Mach 2; When an aircraft is gliding in the air without power, its flight speed is less than Mach 3 and greater than Mach 2. During the in-flight mode transition, the flight speed is less than Mach 3 and greater than Mach 2. When an aircraft is flying at high speed in the air, its speed is between Mach 5 and Mach 3.

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