CN111619823A - Short-distance/vertical take-off and landing aircraft distributed propulsion system test bed - Google Patents
Short-distance/vertical take-off and landing aircraft distributed propulsion system test bed Download PDFInfo
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Abstract
The invention relates to a short-distance/vertical take-off and landing aircraft distributed propulsion system test bed, belonging to the field of aviation; the system comprises a distributed propulsion system, a control system, a rack system and a six-component balance force measuring system; the distributed propulsion system adopts a generator coaxial with the turbojet engine as a power source of the lift fan, the ducted fan and the three-bearing tail nozzle stepping motor, so that a power system closed loop without external energy input is realized, and the actual working state of the short-distance/vertical take-off and landing distributed propulsion system is truly simulated. The systems in the test bed are matched with each other, so that the test research on the power closed loop and the control rule of the short-distance/vertical take-off and landing aircraft distributed propulsion system with different layout requirements can be carried out, the complete thrust data measurement of the short-distance/vertical take-off and landing aircraft distributed propulsion system in a short-distance mode, a horizontal flight mode and a transition state is realized, and the design optimization and control rule research requirements on the short-distance/vertical take-off and landing aircraft distributed propulsion system are met.
Description
Technical Field
The invention belongs to the field of aviation, and particularly relates to a short-distance/vertical take-off and landing aircraft distributed propulsion system test bed which is particularly suitable for short-distance/vertical take-off and landing aircraft distributed propulsion system experimental verification.
Background
In the Ying Ama island war, the ray type vertical take-off and landing fighters defeat first battle, and fighters with short-distance/vertical take-off and landing functions are widely concerned by various major military strong countries. In addition to the British "ray" type of aircraft, the short/VTOL aircraft in active or active service has also been the Jacob-38/41/141 of the former Soviet Union and the AV-8A/B and F-35B of the United states. The all the above-mentioned all-terrain vehicles take off and land on a light aircraft carrier or an amphibious landing ship as a platform, can provide support for air defense and landing operations of a fleet, and are very important equipment in amphibious warfare. The research on short-distance/vertical take-off and landing aircrafts in China is still in the starting stage, and is the research focus in the field of aviation at present.
At present, a lift system applied to a short-distance/vertical take-off and landing fighter mainly comprises a counter-rotating lift fan, a wing root rolling spray pipe, an engine, a three-bearing tail spray pipe and a transmission mechanism, for example, a lift system which is used on F-35B and takes an F136 engine as power output. The tail nozzle can generate 7.1 tons of vertical lift force through deflection, the lift force fan driven by the transmission shaft can generate 9 tons of vertical lift force, and the wing roots at two sides roll the nozzle and can also generate 1.6 tons of lift force through introducing air from the engine, so that short-distance/vertical lifting is realized. However, to handle the large output power, the drive train must be complex and heavy, resulting in a reduced payload, and the root roll nozzle bleed air from the engine also resulting in a reduced engine thrust and efficiency, resulting in a further reduction in payload. How to reduce the weight of the transmission system and improve the propelling efficiency becomes a research hotspot. The distributed propulsion system is used for the short-distance/vertical take-off and landing fighter, can replace a complex and heavy transmission system with a generator and a power transmission system, does not need to bleed air from an engine, reduces the weight of a lift system, and improves the working efficiency of the engine.
The 2018 patent, "a short range or VTOL aerial vehicle employing a distributed power system" (application publication No. CN109911194A) describes a similar propulsion system design. In the research and design process of the propulsion system, tests based on a ground test bed are required to summarize the design and control rules, for example, a patent 'a high-load unmanned helicopter rotor test bed' (application publication No. CN11051048A) published in 2019 introduces a test bed designed for the high-load unmanned helicopter rotor propulsion system, and the test bed consists of a rack, a rotor system, a mechanical transmission system and a measurement and control system. Unlike conventional propulsion systems, the distributed propulsion system is composed of a plurality of propulsion units, and there is no mechanical transmission system in the system, and the generator absorbs part of power from the main propulsion unit (generally referred to as engine) to generate electric energy to drive the sub-propulsion units. The research difficulty of the distributed propulsion system test bed is to simulate the actual working state of the power closed loop of the system and research the control law of the main propulsion unit, the sub-propulsion units and the generator. In particular to a distributed propulsion system of a short-range/vertical take-off and landing aircraft, the components needing to be controlled comprise an engine, a lifting fan, a ducted fan, a generator and a three-bearing tail nozzle, and the related control law is more complex. The common measurement and control system only controls the rotating speed of an engine or the position of a throttle lever and cannot meet the research requirement of the control rule of the distributed propulsion system, so that no related test platform can carry out the test of the short-distance/vertical take-off and landing distributed propulsion system at present and the research and optimization of the control rule of the short-distance/vertical take-off and landing distributed propulsion system can be carried out.
The invention provides a test bed for a distributed propulsion system of a short-distance/vertical take-off and landing aircraft, which aims to simulate the working state of the distributed propulsion system of the short-distance/vertical take-off and landing aircraft, accurately measure the lifting force and the moment generated by the distributed propulsion system and research the control law of the distributed propulsion system of the short-distance/vertical take-off and landing aircraft.
Disclosure of Invention
The technical problem to be solved is as follows:
in order to avoid the defects of the prior art, the invention provides a short-distance/vertical take-off and landing aircraft distributed propulsion system test bed, wherein a generator coaxial with a turbojet engine is adopted by a distributed propulsion system as a power source of a lift fan, a ducted fan and a three-bearing tail nozzle stepping motor, so that a power system closed loop without external energy input is realized, and the actual working state of the short-distance/vertical take-off and landing distributed propulsion system is really simulated. The systems in the test bed are matched with each other, so that the test research on the power closed loop and the control rule of the short-distance/vertical take-off and landing aircraft distributed propulsion system with different layout requirements can be carried out, the complete thrust data measurement of the short-distance/vertical take-off and landing aircraft distributed propulsion system in a short-distance mode, a horizontal flight mode and a transition state is realized, and the design optimization and control rule research requirements on the short-distance/vertical take-off and landing aircraft distributed propulsion system are met.
The technical scheme of the invention is as follows: a short distance/VTOL aircraft distributed propulsion system test bench characterized in that: the system comprises a distributed propulsion system, a control system, a rack system and a six-component balance force measuring system; the six-component balance force measuring system is arranged below the whole test bed and comprises a six-component balance base and a six-component balance fixed on the six-component balance base, the whole test bed is supported by the six-component balance base, and all directions of force and moment generated by the distributed propulsion system are captured by the six-component balance;
the rack system is horizontally arranged at the top of the six-component balance and comprises a test rack, and a lifting force fan bracket, a ducted fan bracket, a generator bracket, an engine bracket and a three-bearing tail nozzle bracket which are fixed on the test rack;
the distributed propulsion system comprises lift fans, ducted fans, a generator, a turbojet engine and a three-bearing tail nozzle, wherein the three-bearing tail nozzle, the turbojet engine and the generator are coaxially mounted at one end of the test bench through a three-bearing tail nozzle support, an engine support and a generator support in sequence from outside to inside;
the control system consists of a control unit and a circuit which are arranged on the generator, wherein the control unit is connected with each component in the distributed propulsion system through the circuit and is used for regulating and controlling the working state of each component in the distributed propulsion system.
The further technical scheme of the invention is as follows: the lifting force fan and the ducted fan are installed in an inverted mode, and air is sucked from the lower side and sprayed upwards.
The further technical scheme of the invention is as follows: the exhaust direction of the three-bearing tail nozzle is adjusted within the range of vertical 90 degrees, upward and horizontal 0 degrees.
The further technical scheme of the invention is as follows: the lift fan adopts a two-stage counter-rotating fan.
The further technical scheme of the invention is as follows: the test bench is of a frame structure, bolt hole groups are arranged at the joints of the test bench and the supports of the components of the distributed propulsion system, the test bench is fixedly connected with the supports of the components of the distributed propulsion system through bolts, and the mounting positions of the supports of the components can be adjusted according to the layout of different distributed propulsion systems.
The further technical scheme of the invention is as follows: the inlet end and the exhaust end of the turbojet engine are respectively connected with the generator and the three-bearing tail nozzle through bolts and are sealed by flange plates.
The further technical scheme of the invention is as follows: the three-bearing tail nozzle comprises a stepping motor, and the spraying angle of the three-bearing tail nozzle is controlled by the driving of the stepping motor.
The further technical scheme of the invention is as follows: the rotor of the generator is coaxial with the rotor of the turbojet engine, and the rotor and the stator of the generator are positioned on a central shaft of the generator; the generator is supported by grid plates arranged in a water shape, and annular grid plates are arranged in the circumferential direction.
The further technical scheme of the invention is as follows: the control unit controls the rotating speed, the output power and the thrust of the turbojet engine by adjusting the position of the throttle lever of the turbojet engine, realizes the control of the power of the generator extracted from the turbojet engine by adjusting the number of turns of the stator coil of the generator, realizes the control of the thrust generated by the lift fan and the ducted fan by adjusting the output power of the generator to the lift fan and the ducted fan, and controls the thrust vector angle of the engine by adjusting the rotating angle of the stepping motor of the three-bearing tail nozzle, thereby finally realizing the adjustment and the control of the working state of each component of the distributed propulsion system.
Advantageous effects
The invention has the beneficial effects that: the generator 6 coaxial with the turbojet engine 8 supplies power to the lift fan 1, the ducted fan 4 and the stepping motor of the three-bearing tail nozzle 11, so that a power closed loop of the distributed propulsion system test bed is realized, external energy is not required to be additionally input, and the real working state of the distributed propulsion system of the short-distance/vertical take-off and landing aircraft is truly simulated. The control unit 15 controls the rotating speed, thrust and output power of the engine 8 by adjusting the position of an accelerator lever of the engine 8, controls the power extracted by the generator 6 from the turbojet engine 8 by adjusting the number of turns of a stator coil in the generator 6, controls the thrust generated by the generator 6 by adjusting the output power of the generator 6 to the lift fan 1 and the ducted fan 4, and controls the thrust vector angle of the engine by adjusting the rotating angle of the generator through a stepping motor of the three-bearing tail nozzle 11, thereby finally realizing the control of the working states of all components of the distributed propulsion system. The adjustable design of the rack system enables the test platform to adapt to the layout requirements of different thrust systems. The six-component balance force measurement system can measure the forces and moments generated by the thrust system in real time and feed back the influence of the forces and moments on the attitude of the aircraft. The system design enables the test to realize the power closed loop of the propulsion system and simultaneously test the control law of each thrust unit, solves the problems that the existing test bench suitable for the distributed propulsion system of the short-distance/vertical take-off and landing aircraft does not realize the power closed loop and the control part is single or incomplete, and provides a basis for developing the design optimization and the control law research of the distributed propulsion system of the short-distance/vertical take-off and landing aircraft under the actual working state.
Drawings
FIG. 1 is a general diagram of a short-range/VTOL aircraft distributed propulsion system test rig;
FIG. 2 is a diagram of distributed propulsion system and control system components;
FIG. 3 is a diagram of gantry system components;
FIG. 4 is a diagram of a six-component balance force measurement system component;
FIG. 5 is a schematic illustration of the mounting of the generator, turbojet engine, three-bearing jet nozzle and control unit;
description of reference numerals: 1. the test bench comprises a lift fan, a lift fan support 2, a ducted fan support 3, a ducted fan support 4, a test bench 5, a power generator 6, a power generator support 7, a turbojet engine 8, an engine support 9, a three-bearing tail nozzle support 10, a three-bearing tail nozzle 11, a six-component balance base 12, a six-component balance 13, a circuit 14 and a control unit 15.
Detailed Description
The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
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.
The invention provides a distributed propulsion system test bed suitable for a short-distance/vertical take-off and landing aircraft, which comprises: the test bench comprises a lift fan 1, a lift fan support 2, a ducted fan support 3, a ducted fan 4, a test bench 5, a generator 6, a generator support 7, a turbojet engine 8, an engine support 9, a three-bearing tail nozzle support 10, a three-bearing tail nozzle 11, a six-component balance base 12, a six-component balance 13, a circuit 14 and a control unit 15. The test bed is mounted in a manner shown in fig. 1. The lift fan 1 is fixed with the test bench 5 through the lift fan bracket 2 by bolts, and similarly, the ducted fan 4, the generator 6, the turbojet engine 8 and the three-bearing tail nozzle 11 are fixed with the test bench 5 through respective brackets by bolts. The distribution positions of all the components are consistent with the installation positions of the distributed thrust system on the short-distance/vertical take-off and landing aircraft. The lift fan 1 is located at the head of the test bed 5, the two ducted fans 3 are located on two sides of the middle of the test bed 5, and the generator 6, the turbojet engine 8 and the three-bearing tail nozzle 11 are located at the tail of the test bed 5. The upper end of the six-component balance 13 is fixedly connected with the bottom of the test bed 5, and the lower end of the six-component balance is fixedly connected with the six-component balance base 12, so that the stability of the whole test system in the test process is ensured.
Further, as shown in fig. 2, the distributed propulsion system includes a lift fan 1, a ducted fan 4, a generator 6, a turbojet engine 8, and a three-bearing jet nozzle 11. The lift fan 1 adopts a two-stage counter-rotating fan, so that the propulsion efficiency and the thrust are further improved. Different from the actual working state of a distributed propulsion system on an aircraft, the lift fan 1 and the ducted fan 4 are installed in an inverted mode, air is sucked from the lower part and is jetted upwards, the exhaust direction of the three-bearing tail nozzle 11 is adjusted within the range of vertical 90 degrees, upward and horizontal 0 degree, and the design is to avoid ablation of high-temperature gas on the ground and influence of near-ground effect on thrust. The rotor of the generator 6 is coaxial with the rotor of the turbojet engine 8, the generator is driven by the engine to generate electric energy, and the electric energy is transmitted to the lift fan 1, the ducted fan 4 and the stepping motor of the three-bearing tail nozzle 11, so that the power closed loop of the whole distributed propulsion system is realized.
Further, as shown in fig. 2, the control system includes a control unit 15 and a line 14. A line 14 connects the control unit 15 with the lift fan 1, the ducted fan 4, the generator 6, the turbojet engine 8 and the three-bearing exhaust nozzle 11. The control unit 15 controls the rotating speed, power and thrust of the engine by adjusting the position of an accelerator lever of the turbojet engine 8, controls the absorbed power of the generator from the turbojet engine by adjusting the number of turns of a stator coil of the generator 6, adjusts the thrust of the lift fan 1 and the thrust of the ducted fan 4 by adjusting the output power of the generator 6 to the lift fan 1, and controls the thrust vector angle of the engine by adjusting the rotating angle of the three-bearing tail nozzle 11. The design of the control system enables all thrust units in the distributed propulsion system to be adjustable and controllable, and the requirements of experimental research on the control rule of the system are met.
Further, as shown in FIG. 3, the gantry system includes a test gantry 5 and a distributed propulsion system component support. The test bench is provided with a bolt hole group for adjusting the position, so that the mounting position of each component support of the distributed propulsion system can be adjusted according to the layout requirement, and the test requirements of the distributed propulsion system with different layouts can be simulated by using the same bench.
Further, as shown in fig. 4, the upper end of the six-component balance 13 is fixedly connected with the test bed 5, and the force and the moment generated by the distributed propulsion system are transmitted to the six-component balance 13 through the test bed 5 for measurement, so as to feed back the influence of the force and the moment on the attitude of the aircraft in real time. The lower end of the six-component balance 13 is fixedly connected with the six-component balance base 12, so that the stability of the whole test system in the test process is kept.
Further, as shown in fig. 5, the tail of the generator 6 is connected with the head of the turbojet engine 8, wherein the connection between the tail of the generator 3 and the turbojet engine 8 is a contraction section. Air enters from an inlet at the front end of the generator 6, and enters an air inlet channel of the turbojet engine 8 after being stabilized by the water-shaped support and the annular grid plate in the generator 6. The generator 6 absorbs power from the turbojet engine 8 to generate electric energy, and then drives the lift fan 1 and the ducted fan 4, so that a power closed loop of the propulsion system is realized.
When the method is specifically implemented, firstly, the six-component balance 13 is installed on the six-component balance base 12 through bolts, and the installation of the six-component balance force measuring system is completed. And then, the test bench 5 is arranged on a six-component balance 13, and the mounting positions of the corresponding supports of the components are selected and arranged according to the layout requirements of the components of the short-distance/vertical take-off and landing distributed propulsion system to complete the arrangement of the bench system. And finally, installing the distributed propulsion system, wherein all the components need to be installed on corresponding supports, the lift fan 1 and the ducted fan 4 only need to be installed on the supports, and the generator 6, the turbojet engine 8 and the three-bearing tail nozzle 11 are connected and assembled with each other firstly, then are connected with the supports respectively and are installed on the test bed 5. Finally, the control unit 15 is connected with the lift fan 1, the ducted fan 4, the generator 6, the turbojet engine 8 and the stepping motors of the three-bearing tail nozzle 11 by using a line 14, so that the installation work of the whole test system is completed.
After the test system is installed, the six-component balance 13 needs to be checked first. When the test system is in a stable state and each thrust unit is in a closed state, the six-component balance 13 is started to perform zero calibration, and standard weights are used for performing calibration. And then, the distributed propulsion system is controlled by the control unit 15, the stator coil of the generator 6 is adjusted to the starting state turn position, the turbojet engine 8 is started to work at a rotating speed, a circuit system for supplying power to the lift fan 1, the ducted fan 4 and the stepping motor of the three-bearing tail nozzle 11 by the generator 6 is tested, and after the whole test system is determined to be in a power closed loop state, test measurement can be started.
The working state of the distributed propulsion system which can be simulated by the test system is determined by the system control rule. The embodiment takes the short-distance/vertical take-off and landing working condition, the transition working condition and the plane flight working condition as examples. Under the working condition of short distance/vertical take-off and landing, the control unit 15 sets the position of an accelerator rod of the turbojet engine 8 to be the maximum, adjusts the power absorbed by the generator 6 and the output power of each component, rotates the angle of the three-bearing tail nozzle to 90 degrees, and switches the system to a short-hanging mode. At this time, the turbojet engine 8 is in the maximum working state, the power absorbed by the generator 6 from the turbojet engine 8 is the maximum, the output power to the lift fan 1 and the ducted fan 4 is also the maximum, the jet flow angle of the three bearing exhaust nozzles 11 is 90 degrees, and the thrust generated by each component is vertical to the ground and upward. According to the forces and moments measured by the six-component balance, the control unit 15 balances the other forces and moments in all directions by controlling the absorbed power of the generator 6 and the output power to each propulsion unit, thereby realizing the balance of the aircraft in the short-range/vertical take-off and landing state. Under the excessive working condition, the control unit 15 maintains the maximum working state of the turbojet engine 8, reduces the number of turns of stator coils of the generator 6 to gradually reduce the absorbed power, reduces the output power of the generator 6 to each power unit, and controls the jet flow angle to gradually change from 90 degrees to 0 degrees through the stepping motor of the three-bearing tail jet pipe 11, at this time, the thrust generated by the lift fan 1 and the ducted fan 4 and facing upwards vertically is gradually reduced, as the absorbed power of the generator 6 is reduced, the thrust of the turbojet engine 8 is increased, and the change of the jet flow direction of the three-bearing tail jet pipe 11 causes the thrust direction generated by the turbojet engine 8 to gradually change from vertical ground to upwards parallel to the ground, and the force generated by the whole distributed propulsion system also changes from vertical upwards to horizontal forwards. Under the flat flight working condition, the control unit 15 reduces the absorbed power of the generator 6 to the minimum, only supplies power to the non-power units of the distributed propulsion system, the jet flow angle of the three-bearing tail nozzle is 0 degree, at the moment, except that the high-temperature high-speed airflow discharged backwards by the turbojet engine 8 generates forward thrust, other power units stop working.
When the distributed propulsion system enters a short-distance/vertical take-off and landing working condition first and is converted into a flat-flight working condition after passing through a moderate working condition, the change mode can simulate the condition that the short-distance/vertical take-off and landing aircraft adopting the distributed propulsion system takes off from ground in a short-distance/vertical mode to flat-flight mode. Similarly, when the aircraft enters a horizontal flight working condition and passes through a short-distance/vertical take-off and landing working condition, the condition that the aircraft is landed from the horizontal flight to the vertical landing can be simulated. Besides the three working conditions mentioned above, the control unit can be adjusted and controlled for each propelling component, and can also carry out related experimental research on other self-designed control rules.
The six-component balance force measurement system measures and captures continuous changes of force and moment generated by the propulsion system in the test process, meets the force measurement requirements of the test on the distributed propulsion system in a complete task period including takeoff, flat flight and landing, and feeds back the influence of the change of the control rule on the thrust generated by the distributed propulsion system.
Through the operation, the distributed propulsion system test bed disclosed by the invention takes the generator coaxial with the turbojet engine as a power supply of the lift fan, the ducted fan and the three-bearing tail nozzle stepping motor, so that the power closed loop of the propulsion system is realized, and the working state of the distributed propulsion system adopted by the short-distance/vertical take-off and landing aircraft can be truly realized. The comprehensive control design and the adjustable design of the test bed of the control unit on the engine, the generator, the ducted fan, the lift fan and the three-bearing tail nozzle enable the test requirements of distributed propulsion systems with different control rules and different power layouts to be met by using the same test bed, the defects that an existing test scheme needs to use an external power supply for power supply, an aircraft power layout is not adjustable, the number of controllable parts is small, the control rules are single are overcome, the cost of carrying out test research on the power layout and the control rules is reduced, and the reliability of a measuring result is improved.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.
Claims (9)
1. A short distance/VTOL aircraft distributed propulsion system test bench characterized in that: the system comprises a distributed propulsion system, a control system, a rack system and a six-component balance force measuring system; the six-component balance force measuring system is arranged below the whole test bed and comprises a six-component balance base and a six-component balance fixed on the six-component balance base, the whole test bed is supported by the six-component balance base, and all directions of force and moment generated by the distributed propulsion system are captured by the six-component balance;
the rack system is horizontally arranged at the top of the six-component balance and comprises a test rack, and a lifting force fan bracket, a ducted fan bracket, a generator bracket, an engine bracket and a three-bearing tail nozzle bracket which are fixed on the test rack;
the distributed propulsion system comprises lift fans, ducted fans, a generator, a turbojet engine and a three-bearing tail nozzle, wherein the three-bearing tail nozzle, the turbojet engine and the generator are coaxially mounted at one end of the test bench through a three-bearing tail nozzle support, an engine support and a generator support in sequence from outside to inside;
the control system consists of a control unit and a circuit which are arranged on the generator, wherein the control unit is connected with each component in the distributed propulsion system through the circuit and is used for regulating and controlling the working state of each component in the distributed propulsion system.
2. The short-range/vertical takeoff and landing aircraft distributed propulsion system test stand of claim 1, wherein: the lifting force fan and the ducted fan are installed in an inverted mode, and air is sucked from the lower side and sprayed upwards.
3. The short-range/vertical takeoff and landing aircraft distributed propulsion system test stand of claim 1, wherein: the exhaust direction of the three-bearing tail nozzle is adjusted within the range of vertical 90 degrees, upward and horizontal 0 degrees.
4. The short-range/vertical takeoff and landing aircraft distributed propulsion system test stand of claim 1, wherein: the lift fan adopts a two-stage counter-rotating fan.
5. The short-range/vertical takeoff and landing aircraft distributed propulsion system test stand of claim 1, wherein: the test bench is of a frame structure, bolt hole groups are arranged at the joints of the test bench and the supports of the components of the distributed propulsion system, the test bench is fixedly connected with the supports of the components of the distributed propulsion system through bolts, and the mounting positions of the supports of the components can be adjusted according to the layout of different distributed propulsion systems.
6. The short-range/vertical takeoff and landing aircraft distributed propulsion system test stand of claim 1, wherein: the inlet end and the exhaust end of the turbojet engine are respectively connected with the generator and the three-bearing tail nozzle through bolts and are sealed by flange plates.
7. The short-range/vertical takeoff and landing aircraft distributed propulsion system test stand of claim 1, wherein: the three-bearing tail nozzle comprises a stepping motor, and the spraying angle of the three-bearing tail nozzle is controlled by the driving of the stepping motor.
8. The short-range/vertical takeoff and landing aircraft distributed propulsion system test stand of claim 1, wherein: the rotor of the generator is coaxial with the rotor of the turbojet engine, and the rotor and the stator of the generator are positioned on a central shaft of the generator; the generator is supported by grid plates arranged in a water shape, and annular grid plates are arranged in the circumferential direction.
9. The short-range/vertical takeoff and landing aircraft distributed propulsion system test stand of claim 1, wherein: the control unit controls the rotating speed, the output power and the thrust of the turbojet engine by adjusting the position of the throttle lever of the turbojet engine, realizes the control of the power of the generator extracted from the turbojet engine by adjusting the number of turns of the stator coil of the generator, realizes the control of the thrust generated by the lift fan and the ducted fan by adjusting the output power of the generator to the lift fan and the ducted fan, and controls the thrust vector angle of the engine by adjusting the rotating angle of the stepping motor of the three-bearing tail nozzle, thereby finally realizing the adjustment and the control of the working state of each component of the distributed propulsion system.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010491690.0A CN111619823A (en) | 2020-06-02 | 2020-06-02 | Short-distance/vertical take-off and landing aircraft distributed propulsion system test bed |
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| CN202010491690.0A CN111619823A (en) | 2020-06-02 | 2020-06-02 | Short-distance/vertical take-off and landing aircraft distributed propulsion system test bed |
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| CN202010491690.0A Pending CN111619823A (en) | 2020-06-02 | 2020-06-02 | Short-distance/vertical take-off and landing aircraft distributed propulsion system test bed |
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| CN115372013A (en) * | 2022-10-26 | 2022-11-22 | 中国空气动力研究与发展中心低速空气动力研究所 | Comprehensive test platform and test method for engine and air entraining system |
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