阅读说明：本技术 一种固定翼垂直起降飞行器升/推一体化动力系统及控制方法 (Lifting/pushing integrated power system of fixed-wing vertical take-off and landing aircraft and control method ) 是由 邓文剑 王占学 周莉 张晓博 史经纬 于 2021-09-07 设计创作，主要内容包括：本发明涉及一种固定翼垂直起降飞行器升/推一体化动力系统及控制方法,通过简单的活门调节,可以同时提供升力和推力。避免了复杂的机构,实现了从垂直起降向平飞状态过渡态简单、可靠；避免了系统的冗余,减小了平飞状态下升力系统造成的废载和废阻,极大的提高了固定翼垂直起降飞行器的空间、重量与气动效率。(The invention relates to a lifting/pushing integrated power system of a fixed-wing vertical take-off and landing aircraft and a control method. A complex mechanism is avoided, and the transition state from the vertical take-off and landing state to the flat flying state is simple and reliable; the redundancy of the system is avoided, the waste load and the waste resistance caused by the lift force system in the flat flight state are reduced, and the space, the weight and the aerodynamic efficiency of the fixed-wing vertical take-off and landing aircraft are greatly improved.)

1. A fixed wing VTOL aircraft lifting/pushing integrated power system is characterized by comprising an impeller (1), an annular volute gas collection chamber (2), a plurality of lifting spray pipes (5), a lifting spray pipe control valve (6), a thrust spray pipe (3) and a thrust spray pipe control valve (4);

the annular volute gas collection chamber (2) is b-shaped, and a cavity is formed inside the annular volute gas collection chamber; the impeller (1) is positioned in the central area; the thrust jet pipe (3) is positioned at the b-shaped port, a thrust jet pipe control valve (4) is arranged at the position, and the nozzle direction of the thrust jet pipe (3) is parallel to the rotating plane of the impeller (1); a plurality of lifting force spray pipes (5) are uniformly distributed on one side of the annular surface of the annular volute gas collection chamber (2), a lifting force spray pipe control valve (6) is arranged at the position, and the nozzle directions of the lifting force spray pipes (5) are vertical to the rotating plane of the impeller (1); high-energy gas generated by rotation of the impeller (1) firstly enters the annular volute gas collection chamber (2) and then respectively enters the lift force spray pipe (5) and the thrust spray pipe (3); the lift force spray pipe control valve and the thrust spray pipe control valve respectively control the outlet areas of the lift force spray pipe and the thrust spray pipe and the jet flow rate of the lift force spray pipe and the thrust spray pipe, so that the lift force and the thrust are respectively controlled.

2. The integrated lift/thrust power system of a fixed-wing VTOL aerial vehicle of claim 1, wherein the magnitude of lift and thrust is controlled by controlling the opening and closing degree of lift nozzle control flap and thrust nozzle control flap, respectively.

3. The lift/push integrated power system of a fixed-wing VTOL aerial vehicle according to claim 1, characterized in that the impeller (1) is of centrifugal or diagonal flow type.

4. The method for controlling the lifting/pushing integrated power system of the fixed-wing VTOL aerial vehicle according to claim 1, wherein the method comprises three stages of control process of the fixed-wing VTOL aerial vehicle from vertical take-off to level flight, hovering in the air or vertical landing:

when the vertical takeoff is carried out to the flat flight stage, the control process comprises the following steps:

step 1: starting the impeller, enabling the impeller (1) to work in a high-rotation-speed state, completely closing the thrust spray pipe control valve (4), completely opening the lift spray pipe control valve (6), and enabling forward thrust to be zero and the lift to reach the maximum value; the aircraft takes off vertically;

step 2: when the aircraft reaches the required height, the aircraft enters a transition state from vertical takeoff to horizontal flight, the rotating speed of the impeller (1) is gradually increased to the maximum rotating speed, meanwhile, the thrust nozzle control valve (4) is gradually opened, the thrust nozzle (3) generates forward thrust, the aircraft gradually accelerates, and the wings gradually generate aerodynamic lift; the lift force of the lift force nozzle pipe (5) is reduced by gradually closing the lift force nozzle pipe control valve (6), until the aerodynamic lift force on the wing is equal to the weight of the aircraft, the lift force nozzle pipe control valve (6) is completely closed, at the moment, the lift force nozzle pipe (5) does not provide any lift force any more, the aircraft finishes the transition state flight, and enters a flat flight state; the speed and the acceleration of the aircraft during flat flight are controlled by adjusting the rotating speed of the impeller (1) and the opening degree of the thrust nozzle control valve (4);

during the hovering stage, the method comprises the following steps:

step 1: gradually closing the thrust nozzle control valve (4) and simultaneously gradually opening the lift nozzle control valve (6);

step 2: when the flying speed is reduced to zero, the thrust nozzle control valve (4) is in a completely closed state, and the opening and closing degree of the lift nozzle control valve (6) is matched with the rotating speed of the impeller (1), so that the lift nozzle (5) provides the lift force required by keeping the aircraft hovering;

during the vertical falling phase, the method comprises the following steps:

step 1: controlling the aircraft to hover in the air above the area to be descended;

step 2: the rotating speed of the impeller (1) and the opening and closing degree of the lift force nozzle control valve (6) are matched and adjusted, so that the lift force provided by the lift force nozzle (5) is smaller than the weight of the aircraft, and the aircraft is ensured to descend at a specified descending speed and land at a certain landing speed.

Technical Field

The invention belongs to the field of vertical take-off and landing aircrafts, and particularly relates to a lifting/pushing integrated power system of a fixed-wing vertical take-off and landing aircraft and a control method.

Background

The vertical take-off and landing aircraft has low requirements on take-off and landing sites, is flexible in arrangement and convenient to use, can realize hovering in the air, has unique performance advantages, is particularly applied to the field of small unmanned aircraft more and more widely, and has increasingly strong requirements in various application fields.

The power system is the key for determining the success or failure and the good or poor performance of the vertical take-off and landing aircraft, the technology of the rotor vertical take-off and landing aircraft gradually tends to be mature and perfect in the field of the rotor vertical take-off and landing aircraft, but the rotor type aircraft has low flying speed, short voyage time, poor stealth performance and the like, and the rotor type aircraft is a performance short board which cannot be overcome. In the field of fixed-wing vertical take-off and landing aircrafts, the power system technology is still in the continuous exploration and development stage.

The existing vertical take-off and landing technology of the fixed-wing aircraft mainly comprises two types, namely a thrust vectoring nozzle, such as a power system of a british' ray type fighter; the second is a thrust vectoring nozzle and lift fan combined power system, such as the power system of the American F-35B fighter. Both types of vertical take-off and landing technologies have inevitable defects, the thrust vectoring nozzle has a complex structure and a very complex control mechanism, and the matching requirement on an engine and the nozzle is very high; the combination of thrust vectoring nozzle and lift fan reduces the difficulty of engine and nozzle matching to some extent, but the lift fan, in addition to functioning during the takeoff and landing and hovering phases, contributes to aircraft drag rejection during other flight phases, occupies installation space, and increases the structural weight of the aircraft.

Therefore, from the existing vertical take-off and landing technology of the fixed-wing aircraft, the problems of complex structure and adjusting mechanism, poor reliability, large waste load capacity and large space are urgently needed to be overcome.

Disclosure of Invention

The technical problem solved by the invention is as follows: based on the technical weakness of the conventional fixed-wing vertical take-off and landing aircraft power system, the invention provides a fixed-wing vertical take-off and landing aircraft power system technology capable of integrally realizing lift force and thrust output.

The technical scheme of the invention is as follows: a fixed wing VTOL aircraft lifting/pushing integrated power system comprises an impeller, an annular volute gas collection chamber, a plurality of lifting force spray pipes, a lifting force spray pipe control valve, a thrust spray pipe and a thrust spray pipe control valve;

the gas collection chamber of the annular volute is b-shaped, and a cavity is formed inside the gas collection chamber; the impeller is positioned in the central area; the thrust jet pipe is positioned at the b-shaped port, a thrust jet pipe control valve is arranged at the b-shaped port, and the direction of a jet orifice of the thrust jet pipe is parallel to the rotating plane of the impeller; a plurality of lift force spray pipes are uniformly distributed on one side of the annular surface of the gas collection chamber of the annular volute, a lift force spray pipe control valve is arranged at the position, and the nozzle direction of each lift force spray pipe is vertical to the rotation plane of the impeller; high-energy gas generated by rotation of the impeller firstly enters an annular volute gas collection chamber and then respectively enters a lift force spray pipe and a thrust spray pipe; the lift force spray pipe control valve and the thrust spray pipe control valve respectively control the outlet areas of the lift force spray pipe and the thrust spray pipe and the jet flow rate of the lift force spray pipe and the thrust spray pipe, so that the lift force and the thrust are respectively controlled.

The further technical scheme of the invention is as follows: the opening and closing degrees of the lift force spray pipe control valve and the thrust spray pipe control valve are controlled to respectively control the magnitude of the lift force and the magnitude of the thrust.

The further technical scheme of the invention is as follows: the impeller is in a centrifugal or diagonal flow type.

The further technical scheme of the invention is as follows: the control method based on the fixed-wing vertical take-off and landing aircraft lifting/pushing integrated power system comprises the control processes of three stages of vertical take-off to level flight, hovering in the air or vertical landing of the fixed-wing vertical take-off and landing aircraft:

when the vertical takeoff is carried out to the flat flight stage, the control process comprises the following steps:

step 1: starting the impeller, wherein the impeller works in a high-rotation-speed state, the thrust spray pipe controls the valve to be completely closed, the lift spray pipe controls the valve to be completely opened, the forward thrust is zero at the moment, and the lift reaches the maximum value; the aircraft takes off vertically;

step 2: when the aircraft reaches the required height, the aircraft enters a transition state from vertical takeoff to horizontal flight, the rotating speed of the impeller is gradually increased to the maximum rotating speed, meanwhile, the thrust nozzle control valve is gradually opened, the thrust nozzle generates forward thrust, the aircraft gradually accelerates, and the wings gradually generate aerodynamic lift; the lift force of the lift force spray pipe is reduced by gradually closing the lift force spray pipe control valve until the aerodynamic lift force on the wing is equal to the weight of the aircraft, the lift force spray pipe control valve is completely closed, at the moment, the lift force spray pipe does not provide the lift force any more, and the aircraft finishes the transition state flight and enters a flat flight state; the speed and the acceleration of the aircraft during flat flight are controlled by adjusting the rotating speed of the impeller and the opening degree of the thrust nozzle control valve;

during the hovering stage, the method comprises the following steps:

step 1: gradually closing the thrust nozzle control valve and simultaneously gradually opening the lift nozzle control valve;

step 2: when the flying speed is reduced to zero, the thrust spray pipe control valve is in a completely closed state, and the opening and closing degree of the lift spray pipe control valve is matched with the rotating speed of the impeller, so that the lift spray pipe provides the lift required by keeping the aircraft hovering;

during the vertical falling phase, the method comprises the following steps:

step 1: controlling the aircraft to hover in the air above the area to be descended;

step 2: the rotating speed of the impeller and the opening and closing degree of the lift force nozzle control valve are adjusted in a matched mode, so that the lift force provided by the lift force nozzle is smaller than the weight of the aircraft, and the aircraft is guaranteed to descend at a specified descending speed and land at a certain landing speed.

Effects of the invention

The invention has the technical effects that: in the foregoing analysis, it is mentioned that the existing vertical take-off and landing technology of the fixed-wing aircraft relies on the thrust vectoring nozzle and the lift fan, and they have the problems of insurmountable high complexity of the structure and the adjusting mechanism, poor reliability, and large waste carrying capacity and space. The thrust jet pipe 3 and the lift jet pipe 5 of the invention do not need to be adjusted and have no adjusting mechanism on the main body part of the jet pipe, and only simple thrust jet pipe control valve 4 and lift jet pipe control valve 6 are respectively arranged in the thrust jet pipe 3 and the lift jet pipe 5, and the conversion of the lift force and the thrust force in any proportion can be realized by matching and adjusting the opening degree of the thrust jet pipe control valve 4 and the lift jet pipe control valve 6 and the rotating speed of the impeller 1. The method avoids complex mechanisms, and realizes simple and reliable conversion among vertical take-off and landing, hovering in the air and flying in the plane. Reliability and convenience between flight state conversion can be greatly improved, waste load and waste resistance caused by redundant components of a lift system in a flat flight state are reduced, and therefore spatial arrangement, weight and aerodynamic efficiency of the fixed-wing vertical take-off and landing aircraft are improved, and reliability of the whole aircraft is also improved.

Drawings

FIG. 1 is a front view of a lift/push integrated power system of a fixed-wing VTOL aerial vehicle

FIG. 2 is a bottom view of the lifting/pushing integrated power system of the fixed-wing VTOL aerial vehicle

FIG. 3 is a diagram of a typical example of a fixed wing VTOL aircraft with an integrated lift/push powertrain

Description of reference numerals: 1-an impeller; 2-annular volute gas collection chamber; 3-a thrust nozzle; 4-thrust nozzle control valve; 5-a lift force spray pipe; 6-lift force spray pipe control valve.

Detailed Description

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like, indicate orientations and positional relationships based on those shown in the drawings, and are used only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be considered as limiting the present invention.

Referring to fig. 1-3, a lift/push integrated power system for a fixed-wing VTOL aerial vehicle comprises: centrifugal or diagonal flow impellers, which work the airflow to improve the mechanical energy of the airflow; the annular volute gas collection chamber is used for allowing high-energy gas flow flowing out of the impeller to enter the volute gas collection chamber; the lift force spray pipes are arranged at equal intervals along the circumferential direction of the volute collection chamber, and when high-energy airflow is sprayed out from the lift force spray pipes, the vertical upward lift force is generated; the lift force spray pipe controls the valve to control the outlet area of the lift force spray pipe so as to control the airflow flow of the lift force spray pipe and further control the lift force; the thrust jet pipe is a radial or tangential outlet of airflow from the annular volute gas collection chamber, and when high-energy gas is ejected from the thrust jet pipe, forward thrust is generated; the thrust jet pipe controls the valve to control the outlet area of the thrust jet pipe so as to control the airflow flow of the thrust jet pipe and control the thrust.

Furthermore, the centrifugal or diagonal flow impeller does work on the airflow, improves the flow velocity or total pressure of the airflow, and provides energy for generating jet flow lifting force and jet flow thrust.

Further, the annular volute plenum surrounds the impeller, and the high-energy airflow coming out of the impeller firstly enters the annular volute plenum.

Furthermore, the lift force spray pipe is circumferentially arranged on one side of the annular volute gas collection chamber, the nozzle direction is perpendicular to the impeller rotation plane, and when the lift force spray pipe controls the valve to be opened, airflow is sprayed out from the lift force spray pipe to generate upward lift force.

Further, the thrust jet pipe jets airflow backwards to generate forward thrust.

Furthermore, the opening and closing degrees of the lift force spray pipe control valve and the thrust spray pipe control valve are controlled to respectively control the magnitude of the lift force and the magnitude of the thrust.

The invention provides a fixed wing VTOL aircraft lifting/pushing integrated power system, as shown in fig. 1 and 2, comprising: the device comprises a centrifugal or oblique flow impeller 1, an annular volute gas collection chamber 2, a thrust spray pipe 3, a thrust spray pipe control valve 4, a lift spray pipe 5 and a lift spray pipe control valve 6.

FIG. 3 provides an exemplary illustration of a fixed wing VTOL aerial vehicle incorporating the power system of the present invention. The invention fully utilizes the advantages of strong single-stage supercharging capacity, wide flow and pressure ratio adjusting range, wide efficient working range, stable and reliable performance and the like of the centrifugal or oblique flow impeller 1 as an acting component for airflow, is used for improving the flow speed or total pressure of the airflow, converges the high-energy airflow passing through the impeller 1 into the annular volute collection chamber 2, and then outwards sprays the airflow through the lift force spray pipe 5 or the thrust spray pipe 3 to generate lift force or thrust. The flow of the lift force spray pipe 5 and the flow of the thrust spray pipe 3 are respectively controlled by the lift force spray pipe control valve 6 and the thrust spray pipe control valve 4, so that the control of the lift force and the thrust is realized.

In the vertical takeoff stage, the impeller 1 works in a high-rotation-speed state, the thrust nozzle control valve 4 is completely closed, the lift nozzle control valve 6 is completely opened, the forward thrust is zero at the moment, and the lift reaches the maximum value. When the aircraft reaches a certain height, the aircraft starts to enter a transition state from vertical takeoff to flat flight, the rotating speed of the impeller 1 is gradually increased to the maximum, meanwhile, the thrust spray pipe control valve 4 is gradually opened, the thrust spray pipe 3 generates forward thrust, the aircraft gradually accelerates, aerodynamic lift is gradually generated on wings, the lift of the lift spray pipe 5 is reduced by gradually closing the lift spray pipe control valve 6 according to the principle that the total lift is balanced with the total weight of the aircraft, when the aerodynamic lift on the wings is equal to the weight of the aircraft, the lift spray pipe control valve 6 is completely closed, the lift spray pipe 5 does not provide lift any more, the aircraft finishes transition state flight, and enters the flat flight state. The speed and the acceleration of the aircraft during flat flight are controlled by adjusting the rotating speed of the impeller 1 and the opening degree of the thrust nozzle control valve 4.

When the aircraft is suspended in the air, the thrust nozzle control valve 4 is gradually closed, and the lift nozzle control valve 6 is gradually opened, so that the flight speed is gradually reduced, and the resistance and the pneumatic lift of the aircraft body are gradually reduced, therefore, the opening and closing degree of the thrust nozzle control valve 4 and the lift nozzle control valve 6 and the rotating speed of the impeller 1 are matched and adjusted according to flight resistance and lift requirements. When the flying speed is reduced to zero, the thrust nozzle control valve 4 is in a completely closed state, and the opening and closing degree of the lift nozzle control valve 6 is matched with the rotating speed of the impeller 1, so that the lift nozzle 5 provides the lift force required by keeping the aircraft hovering.

When the aircraft is to realize vertical landing, firstly controlling the aircraft to hover in the air above an area to be landed; then, the rotating speed of the impeller 1 and the opening and closing degree of the lift force nozzle control valve 6 are matched and adjusted at the same time, so that the lift force provided by the lift force nozzle 5 is smaller than the weight of the aircraft, and the aircraft is ensured to descend at a specified descending speed and land at a certain landing speed.