Power system suitable for small vertical take-off and landing fixed wing aircraft
阅读说明：本技术 一种适用于小型垂直起降固定翼飞行器的动力系统 (Power system suitable for small vertical take-off and landing fixed wing aircraft ) 是由 王子安 龚正 刘朋辉 王欣艺 吕慧涛 张同任 于 2019-09-20 设计创作，主要内容包括：一种适用于小型垂直起降固定翼飞行器的动力系统,包括两个独立的动力子系统,分别是：升力风扇和辅助电机动力子系统,由该系统产生向下喷出的气流,从而产生位于机身前部的第一垂直升力；主涵道风扇和主电机动力子系统,通过一个矢量喷管将主涵道风扇向后喷出的气体向下偏转,产生位于机身尾部的第二垂直升力；偏流系统,通过两个滚转喷管将主涵道风扇产生的压缩空气分别引至两侧机翼,再通过翼尖上的喷口向下喷出,从而产生位于两侧机翼处的第三垂直升力。两个滚转喷管内设有气流调节机构,所述气流调节机构用以调节两个滚转喷管的喷气量,从而产生滚转力矩；通过偏转第一喷管单元将向下喷出的气体顺时针或逆时针偏转,从而产生偏航力矩。(A power system suitable for a small vertical take-off and landing fixed wing aircraft comprises two independent power subsystems, namely: the lift fan and auxiliary motor power subsystem generates downward sprayed airflow so as to generate a first vertical lift force at the front part of the fuselage; the main ducted fan and the main motor power subsystem deflect the gas ejected backwards by the main ducted fan downwards through a vectoring nozzle to generate a second vertical lift force positioned at the tail part of the machine body; and the bias flow system guides the compressed air generated by the main ducted fan to the wings on the two sides respectively through the two rolling spray pipes and then downwards sprays the compressed air through the nozzles on the wing tips, so that third vertical lift forces positioned on the wings on the two sides are generated. The two rolling spray pipes are internally provided with airflow adjusting mechanisms which are used for adjusting the air injection amount of the two rolling spray pipes so as to generate rolling torque; the downwardly ejected gas is deflected clockwise or counterclockwise by deflecting the first nozzle unit, thereby generating a yawing moment.)
1. A power system suitable for a small vertical take-off and landing fixed wing aircraft is characterized by comprising two independent power subsystems, wherein the two independent power subsystems are respectively as follows:
the lift fan and auxiliary motor power subsystem is arranged on the front fuselage section, and the system generates downward sprayed airflow so as to generate a first vertical lift force positioned at the front part of the fuselage;
the main ducted fan and the main motor power subsystem deflect the gas ejected backwards by the main ducted fan downwards through a vectoring nozzle to generate a second vertical lift force positioned at the tail part of the machine body;
the bias flow system is used for guiding compressed air generated by the main ducted fan to wings on two sides respectively through the two rolling spray pipes and downwards spraying the compressed air through nozzles on the wing tips so as to generate third vertical lift force at the wings on the two sides;
the two rolling spray pipes are internally provided with airflow adjusting mechanisms, each airflow adjusting mechanism comprises a driving device arranged on the outer wall of the flow guide cylinder and a blocking device arranged inside the joint of the rolling spray pipe and the flow guide cylinder, and the driving devices drive the blocking devices to adjust the size of airflow inlets of the rolling spray pipes so as to adjust the air injection amount of the two rolling spray pipes and generate rolling torque;
and the gas sprayed backwards by the main ducted fan is deflected clockwise or anticlockwise through the vectoring nozzle, so that a yawing moment is generated.
2. The power system for a small vtol fixed wing aircraft according to claim 1, wherein: the main ducted fan and the main motor power subsystem comprise two main air inlet channels, an auxiliary air inlet channel, a flow guide cylinder and a vectoring nozzle, wherein the two main air inlet channels are symmetrically arranged at two sides of the front end of the machine body;
the vectoring nozzle includes the spray tube unit that a plurality of both ends cross section diameters are the same, the spray tube unit with all connect through the spray tube coupling mechanism that the structure is the same between the water conservancy diversion barrel and between per two spray tube units, and connect the back, each spray tube unit can realize mutual rotation, and at rotatory in-process, the axis of each spray tube unit is in the coplanar all the time, spray tube coupling mechanism includes:
the annular bearing seat is fixedly connected to one end of the spray pipe unit or one end of the flow guide cylinder body;
the gear ring is fixedly connected to the other end of the spray pipe unit;
the V-shaped bearings are connected between the annular bearing seat and the gear ring, and a V-shaped guide rail matched with the V-shaped bearings is arranged on the gear ring;
the steering engine mounting seat is fixedly arranged on one side of the annular bearing seat, a steering engine is mounted on the steering engine mounting seat, and a pinion meshed with the gear ring is arranged on a driving shaft of the steering engine;
the tail part of the last section of spray pipe unit on the vectoring spray pipe is provided with a tapered tail nozzle.
3. The power system for a small vertical take-off and landing fixed wing aircraft according to claim 2, wherein: the V-shaped bearings are uniformly arranged on the circumference of the annular bearing seat, the inner ring of each V-shaped bearing is fixedly connected with the annular bearing seat through a fixed pin shaft, and the outer ring of each V-shaped bearing is matched with the V-shaped guide rail of the gear ring.
4. The power system for a small vertical take-off and landing fixed wing aircraft according to claim 2, wherein: the vectoring nozzle comprises a first nozzle unit, a second nozzle unit and a third nozzle unit, wherein the first nozzle unit, the second nozzle unit and the third nozzle unit are all of pipe-type structures with oval cross sections, the front end of the first nozzle unit is of a spout structure with a round cross section and is connected with the tail end of the flow guide cylinder body, the tail end of the first nozzle unit, the front end and the tail end of the second nozzle unit and the front end of the third nozzle unit are of inclined plane structures with round inclined cross sections, and the tail end of the third nozzle unit is of a spout structure with a round cross section and is connected with a tail spout with a gradually reduced cross section.
5. The power system for a small VTOL fixed-wing aircraft according to claim 4, wherein: the included angle alpha between the oblique section of the joint of the first spray pipe unit and the second spray pipe unit and the oblique section of the joint of the second spray pipe unit and the third spray pipe unit and the cross section of the spray pipe is obtained by the following formula:
where β is a deflection angle of the air flow when the vectoring nozzle reaches the maximum deflection state, and α is 22.5 ° when β is 90 °.
6. The power system for a small VTOL fixed-wing aircraft according to claim 4, wherein: o-shaped sealing rings are arranged between the annular bearing seat and the V-shaped guide rail at the joint of the diversion cylinder body and the first spray pipe unit, between the annular bearing seat and the V-shaped guide rail at the joint of the first spray pipe unit and the second spray pipe unit, and between the annular bearing seat and the V-shaped guide rail at the joint of the second spray pipe unit and the third spray pipe unit.
Technical Field
The invention relates to a power system suitable for a small vertical take-off and landing fixed wing aircraft, and belongs to the technical field of aviation aircraft design.
Background
The vertical take-off and landing fixed wing aircraft can take off in a short distance, then is converted into a fixed wing mode to fly, finally lands vertically, integrates the vertical take-off and landing and hovering control capabilities of the rotor aircraft and the advantages of high speed, long range and the like of the fixed wing aircraft, and is a hotspot of research in various countries in recent years.
The combined power system has the advantages that the combined power system has a complex structure and large weight, two power subsystems are controlled by one motor, and a clutch system needs to be transmitted.
In combined driving system, generally use the thrust vectoring nozzle technique to realize VTOL, three bearing thrust vectoring nozzles are the big corner thrust vectoring nozzle that is applied to VTOL fixed wing aircraft, realize the deflection of the whole profile of spray tube through mutual rotation between the three-section spray tube, use the thrust vectoring nozzle can reduce the requirement and the deployment degree of difficulty to the take off and land place, improve VTOL fixed wing aircraft's viability greatly, but the geometric structure of vectoring nozzle is complicated, the function is single, weight is big, can't satisfy multiple flight condition.
Disclosure of Invention
In view of the problems in the prior art, the invention provides a power system suitable for a small vertical take-off and landing fixed-wing aircraft. The control of vertical take-off and landing, horizontal flight, pitching, rolling, yawing and the like can be realized by adjusting the motor rotating speeds of the lift fan and auxiliary motor power subsystem, the main ducted fan and the main motor power subsystem and controlling the rolling spray pipe and the vectoring spray pipe through the steering engine.
The invention adopts the following technical scheme:
a power system suitable for a small vertical take-off and landing fixed wing aircraft comprises two independent power subsystems, namely:
the lift fan and auxiliary motor power subsystem is arranged on the front fuselage section, and the system generates downward sprayed airflow so as to generate a first vertical lift force positioned at the front part of the fuselage;
the main ducted fan and the main motor power subsystem deflect the gas ejected backwards by the main ducted fan downwards through a vectoring nozzle to generate a second vertical lift force positioned at the tail part of the machine body;
and the bias flow system guides the compressed air generated by the main ducted fan to the wings on the two sides respectively through the two rolling spray pipes and then downwards sprays the compressed air through the nozzles on the wing tips, so that third vertical lift forces positioned on the wings on the two sides are generated.
The two rolling spray pipes are internally provided with airflow adjusting mechanisms, each airflow adjusting mechanism comprises a driving device arranged on the outer wall of the flow guide cylinder and a blocking device arranged inside the joint of the rolling spray pipe and the flow guide cylinder, and the driving devices drive the blocking devices to adjust the size of airflow inlets of the rolling spray pipes so as to adjust the airflow spraying amount of the two rolling spray pipes and generate rolling torque;
and the gas sprayed backwards by the main ducted fan is deflected clockwise or anticlockwise through the vectoring nozzle, so that a yawing moment is generated.
The main ducted fan and the main motor power subsystem comprise two main air inlet channels, an auxiliary air inlet channel, a flow guide cylinder and a vectoring nozzle, wherein the two main air inlet channels are symmetrically arranged at two sides of the front end of the machine body;
the vectoring nozzle includes the spray tube unit that a plurality of both ends cross section diameters are the same, the spray tube unit with all connect through the spray tube coupling mechanism that the structure is the same between the water conservancy diversion barrel and between per two spray tube units, and connect the back, each spray tube unit can realize mutual rotation, and at rotatory in-process, the axis of each spray tube unit is in the coplanar all the time, spray tube coupling mechanism includes:
the annular bearing seat is fixedly connected to one end of the spray pipe unit or one end of the flow guide cylinder body;
the gear ring is fixedly connected to the other end of the spray pipe unit;
the V-shaped bearings are connected between the annular bearing seat and the gear ring, and a V-shaped guide rail matched with the V-shaped bearings is arranged on the gear ring;
the steering engine mounting seat is fixedly arranged on one side of the annular bearing seat, a steering engine is mounted on the steering engine mounting seat, and a pinion meshed with the gear ring is arranged on a driving shaft of the steering engine;
the tail part of the last section of spray pipe unit on the vectoring spray pipe is provided with a tapered tail nozzle.
The V-shaped bearings are uniformly arranged on the circumference of the annular bearing seat, the inner ring of each V-shaped bearing is fixedly connected with the annular bearing seat through a fixed pin shaft, and the outer ring of each V-shaped bearing is matched with the V-shaped guide rail of the gear ring.
The vectoring nozzle comprises a first nozzle unit, a second nozzle unit and a third nozzle unit, wherein the first nozzle unit, the second nozzle unit and the third nozzle unit are all of pipe-type structures with oval cross sections, the front end of the first nozzle unit is of a spout structure with a round cross section and is connected with the tail end of the flow guide cylinder body, the tail end of the first nozzle unit, the front end and the tail end of the second nozzle unit and the front end of the third nozzle unit are of inclined plane structures with round inclined cross sections, and the tail end of the third nozzle unit is of a spout structure with a round cross section and is connected with a tail spout with a gradually reduced cross section.
The included angle alpha between the oblique section of the joint of the first spray pipe unit and the second spray pipe unit and the oblique section of the joint of the second spray pipe unit and the third spray pipe unit and the cross section of the spray pipe is obtained by the following formula:
wherein beta is the airflow deflection angle when the vectoring nozzle reaches the maximum deflection state. When β is 90 °, α is 22.5 °.
O-shaped sealing rings are arranged between the annular bearing seat and the V-shaped guide rail at the joint of the diversion cylinder body and the first spray pipe unit, between the annular bearing seat and the V-shaped guide rail at the joint of the first spray pipe unit and the second spray pipe unit, and between the annular bearing seat and the V-shaped guide rail at the joint of the second spray pipe unit and the third spray pipe unit.
The invention has the following beneficial effects:
(1) the lift fan and auxiliary motor power subsystem, the main ducted fan and the main motor power subsystem are two independent power subsystems, and a transmission clutch system is not needed.
(2) The first spray pipe unit, the second spray pipe unit and the third spray pipe unit are rotated, so that the axis of the tail nozzle and the axis of the flow guide cylinder body form an angle of 0-90 degrees in a symmetrical plane, and the first spray pipe unit is rotated, so that an angle of 0-20 degrees is formed between the axis of the tail nozzle and the symmetrical plane.
(3) By controlling the motor and the steering engine, the control of vertical take-off and landing, horizontal flying, pitching, rolling, yawing and the like can be realized.
(4) The structure complexity is simplified, the structure weight is reduced, and the efficiency of the power system of the vertical take-off and landing fixed wing aircraft is improved.
Drawings
Fig. 1 is a schematic view of the overall structure of the present invention.
FIG. 2 is a schematic structural view of the vectoring nozzle mechanism of the present invention.
FIG. 3 is a schematic vertical cross-sectional view of a vectoring nozzle of the present invention.
Fig. 4 is a schematic structural view of a joint of the guide cylinder and the first nozzle unit in the present invention.
Fig. 5 is a partial sectional view of the junction of the draft tube body and the first nozzle unit in the present invention.
Fig. 6 is a schematic horizontal view of the jet nozzle.
FIG. 7 is a schematic view of the jet nozzle directed vertically downward.
Fig. 8 is a schematic view of the tail nozzle rotating 20 degrees clockwise in a vertical lifting state.
Wherein:
1-a lift fan and auxiliary motor power subsystem, 2-a main air inlet channel, 3-an auxiliary air inlet channel, 4-a main ducted fan, 5-a guide cylinder body, 6-a rolling spray pipe, 7-a rolling control and adjustment mechanism, 8-a vector spray pipe, 9-a first spray pipe unit, 10-a second spray pipe unit, 11-a third spray pipe unit, 12-a tail spray nozzle, 13-a first spray pipe unit steering engine mounting seat, 14-a second spray pipe unit steering engine mounting seat, 15-a third spray pipe unit steering engine mounting seat, 16-a first spray pipe unit steering engine, 17-a second spray pipe unit steering engine, 18-a third spray pipe unit steering engine, 19-a first spray pipe unit pinion, 20-a second spray pipe unit pinion, 21-a third spray pipe unit pinion, 22-a first spray pipe unit gear ring, 23-a second spray pipe unit gear ring, 24-a third spray pipe unit gear ring, 25-an annular bearing seat at the joint of a guide cylinder body and a first spray pipe unit, 26-an annular bearing seat at the joint of the first spray pipe unit and a second spray pipe unit, 27-an annular bearing seat at the joint of the second spray pipe unit and a third spray pipe unit, 28-a V-shaped bearing at the joint of the guide cylinder body and the first spray pipe unit, 29-a V-shaped bearing at the joint of the first spray pipe unit and the second spray pipe unit, 30-a V-shaped bearing at the joint of the second spray pipe unit and the third spray pipe unit, 31-a V-shaped guide rail at the joint of the guide cylinder body and the first spray pipe unit, 32-a V-shaped guide rail at the joint of the first spray pipe unit and the second spray pipe unit, and 33-a V-shaped guide rail at, 34-bolt at bearing seat and 35-nut at bearing seat.
Detailed Description
Referring to fig. 1, the power system of the invention for a small vertical take-off and landing fixed wing aircraft comprises two independent power subsystems, namely a lift fan and auxiliary motor power subsystem 1 and a main ducted fan and main motor power subsystem, and a bias flow system.
The power subsystem 1 of the lift fan and the auxiliary motor is arranged on the front fuselage section; the main ducted fan and main motor power subsystem comprises two main
Referring to FIG. 2, the
The throat of the
The first
The
Referring to fig. 3, the included angle α between the oblique section at the junction of the first and
where β is a deflection angle of the air flow when the vectoring nozzle reaches the maximum deflection state, and α is 22.5 ° when β is 90 °.
Referring to fig. 4 and 5, two first nozzle unit steering
Referring to fig. 1, 6 to 8, the power system for a small vertical take-off and landing fixed-wing aircraft can meet different flight conditions and functional requirements, and the efficiency of the power system for the vertical take-off and landing fixed-wing aircraft is improved.
When the fixed-wing aircraft is in a flat flight state, an upper cover plate of a lift fan and an auxiliary motor power subsystem 1 on the back of the fixed-wing aircraft and an upper cover plate of an auxiliary air inlet channel 3 are closed, and a first
When the fixed-wing aircraft is in a vertical take-off and landing state, an upper cover plate of a lift fan and an auxiliary motor power subsystem 1 on the back of the fixed-wing aircraft and an upper cover plate of an auxiliary air inlet 3 are opened, a first spray pipe
The foregoing is only a preferred embodiment of this invention and it should be noted that modifications can be made by those skilled in the art without departing from the principle of the invention and these modifications should also be considered as the protection scope of the invention.
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