CN113415412B - Wide-speed-range jet flow control aircraft - Google Patents
Wide-speed-range jet flow control aircraft Download PDFInfo
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- CN113415412B CN113415412B CN202110710139.5A CN202110710139A CN113415412B CN 113415412 B CN113415412 B CN 113415412B CN 202110710139 A CN202110710139 A CN 202110710139A CN 113415412 B CN113415412 B CN 113415412B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
- B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
- B64C21/025—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for simultaneous blowing and sucking
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C15/00—Attitude, flight direction, or altitude control by jet reaction
- B64C15/02—Attitude, flight direction, or altitude control by jet reaction the jets being propulsion jets
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C30/00—Supersonic type aircraft
Abstract
The invention provides a jet flow control aircraft with a wide speed range, which comprises an aircraft body and wings arranged on the left side and the right side of the aircraft body; flow separation inhibiting devices are distributed on the front edge of each wing along the spanwise direction of the wing, and are used for inhibiting flow separation on the surface of the wing; the rear edge of the outer side of each wing is provided with an adjustable nozzle circulation control device to provide rolling control for the aircraft; and a binary jet thrust vector device is arranged in the middle of the rear end of the aircraft body, and is used for pitch and yaw control in wide-speed-range flight. The invention solves the problem of failure control of the three-axis attitude of the existing aircraft without control surfaces in the low-speed large-attack-angle and high-subsonic-speed flight states.
Description
Technical Field
The invention belongs to the technical field of aviation systems, and particularly relates to a wide-speed-range jet control aircraft.
Background
Flight vehicles without control surfaces exhibit a number of advantages, such as the substitution of pure jet control for conventional mechanical deflection control surfaces: (1) less volume and weight is occupied; (2) lower equipment manufacturing and maintenance costs; (3) Removing micro-holes and slits on the aircraft outer mold line to reduce gap flow noise; (4) Stealth characteristics are improved for aircraft handling and trim.
Some existing flight vehicles without control surfaces provide pitching, rolling and yawing attitude control moments by simply utilizing different jet flow combination modes of the trailing edge circular control wings. When an aircraft flies at a low speed and a large attack angle, the conventional trailing edge circulation control technology cannot effectively control the flow around the wing due to flow separation. When the aircraft flies at high subsonic speed, the control efficiency of the trailing edge circulation is obviously reduced and even completely fails.
Still other existing aircraft without control surfaces utilize jet thrust vectors to provide pitch moments, trailing edge ring control wings to provide roll moments, and wing tip counter jets to provide yaw moments. And when the main flow and the jet flow at transonic speed, the deflection of the main flow is difficult to realize, and the thrust vector is invalid. Therefore, the existing aircraft without the control surface has difficulty in maintaining effective three-axis attitude control in wide-speed-range flight.
In view of the above, a control surface-free aircraft is designed to enhance the three-axis attitude control capability in wide-speed-range flight, which is a technical problem that improvement is urgently needed in the field of current aviation control systems.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides a wide-speed-domain jet flow control aircraft, which solves the problem of failure of triaxial attitude control of the existing aircraft without control surfaces in low-speed large-attack-angle and high-subsonic-speed flight states.
In order to achieve the technical purpose, the technical scheme provided by the invention is as follows:
the wide-speed-range jet flow control aircraft comprises an aircraft body and wings arranged on the left side and the right side of the aircraft body;
flow separation inhibiting devices are distributed on the front edge of each wing along the spanwise direction of the wing, and are used for inhibiting flow separation on the surface of the wing;
the rear edge of the outer side of each wing is provided with an adjustable nozzle circulation control device to provide rolling control for the aircraft;
and a binary jet thrust vector device is arranged in the middle of the rear end of the airplane body, and is used for pitch and yaw control in wide-speed-range flight.
As a further improvement of the invention, the flow separation suppression devices on the left and right airfoils are distributed in bilateral symmetry. The flow separation suppression device comprises a plurality of synthetic jet actuators, each synthetic jet actuator is arranged in a wing, synthetic jet nozzles of each synthetic jet actuator are uniformly arranged on the surface of the front edge of each wing along the unfolding direction of the wing, and gas is periodically blown out or sucked in through the synthetic jet nozzles of each synthetic jet actuator, so that the flow separation on the surface of the wing is suppressed.
As a further improvement of the invention, the synthetic jet actuator comprises a synthetic jet cavity, a piezoelectric vibrator, a vibrating diaphragm and a synthetic jet nozzle, wherein the synthetic jet cavity is an oblate cylindrical cavity, the piezoelectric vibrator is attached to the vibrating diaphragm, the vibrating diaphragm is used as the upper surface of the synthetic jet cavity, the synthetic jet nozzle is a slender slit, and the length direction of the synthetic jet nozzle is consistent with the unfolding direction of the machine body; the synthetic jet nozzle is communicated with the synthetic jet cavity; under the excitation of an electric signal, the piezoelectric vibrator drives the vibrating diaphragm to vibrate to change the volume of the synthetic jet cavity, so that the synthetic jet nozzle periodically blows out or sucks in gas. Further, the piezoelectric vibrator is a piezoelectric ceramic or other electrically-excited braking material.
As a further improvement of the invention, the outer side rear edges of the left wing and the right wing are respectively provided with an adjustable nozzle circulation control device, and the two adjustable nozzle circulation control devices on the left wing and the right wing are distributed in a bilateral symmetry way.
As a further improvement of the invention, the adjustable nozzle circulation control device adopts an adjustable nozzle circulation control actuator. The adjustable nozzle circulation control exciter comprises a circulation control exciter shell, a circulation control lower air chamber, a circulation control upper air chamber, a piezoelectric contraction block, a circulation control lower nozzle, a circulation control upper nozzle and a coanda trailing edge. The adjustable nozzle circulation control device is arranged in the corresponding notches of the outer side rear edges of the left wing and the right wing and is seamlessly connected with the wings to form a part of the wings, so that the aerodynamic appearance of the aircraft is not influenced.
The environment-friendly energy-saving control device is characterized in that the interior of the shell of the environment-friendly quantity control exciter is divided into two independent air chambers which are symmetrical up and down by a middle partition plate, the two independent air chambers are respectively an environment-friendly quantity control upper air chamber and an environment-friendly quantity control lower air chamber, the front parts of the air chambers of the environment-friendly quantity control upper air chamber and the environment-friendly quantity control lower air chamber are respectively communicated with an environment-friendly quantity control bleed air pipeline through corresponding environment-friendly quantity control electromagnetic valves, and the environment-friendly quantity control bleed air pipeline is connected with a bleed air source and introduces high-pressure air from the bleed air source into the environment-friendly quantity control upper air chamber and the environment-friendly quantity control lower air chamber; the rear parts of the air chambers of the upper and lower annular quantity control air chambers are respectively communicated with the corresponding upper annular quantity control nozzles and lower annular quantity control nozzles, the end of the intermediate partition plate is connected with a coanda trailing edge, and the coanda trailing edge is positioned between the upper annular quantity control nozzles and the lower annular quantity control nozzles.
High-pressure gas from a bleed air source enters the annular quantity control upper air chamber and the annular quantity control lower air chamber through the annular quantity control solenoid valve through the annular quantity control bleed air pipeline and is ejected from the annular quantity control upper nozzle and the annular quantity control lower nozzle. Under the action of the flowing coanda effect, the jet flow is attached to the coanda trailing edge to generate entrainment on the flow of the boundary layer on the surface of the wing, so that the annular volume of the wing is changed, and the lift force is further changed. When the ring volume control upper nozzle of the left wing trailing edge adjustable nozzle ring volume control exciter and the ring volume control lower nozzle of the right wing trailing edge adjustable nozzle ring volume control exciter work, the lift force of the left wing is increased, the lift force of the right wing is reduced, and control torque for enabling the aircraft to roll rightwards is generated. On the contrary, when the upper annular volume control nozzle of the right wing trailing edge adjustable nozzle annular volume control exciter and the lower annular volume control nozzle of the left wing trailing edge adjustable nozzle annular volume control exciter work, the lift force of the right wing is increased, the lift force of the left wing is reduced, and control torque for enabling the aircraft to roll leftwards is generated.
As a further improvement of the invention, the middle partition board is a telescopic partition board, the middle partition board is provided with a piezoelectric telescopic block, the piezoelectric telescopic block is excited by an electric signal, and the piezoelectric telescopic block contracts to further drive the coanda trailing edge to contract. When the piezoelectric telescopic block is not excited by electric signals, the coanda trailing edge between the ring volume control upper nozzle and the ring volume control lower nozzle enables the ring volume control upper nozzle and the ring volume control lower nozzle to be convergent nozzles. When the piezoelectric telescopic block is excited by applying an electric signal, the piezoelectric telescopic block contracts, the coanda trailing edge contracts, and the annular quantity control upper nozzle and the annular quantity control lower nozzle are changed into a convergent divergent nozzle. When the aircraft flies at high subsonic speed, an electric signal is applied to the piezoelectric telescopic block for excitation, airflow is changed into supersonic jet flow through the convergent-divergent nozzle, the jet flow is not easy to separate from a coanda trailing edge after the pressure of the air chamber is increased, the flowing wall attachment effect is enhanced, and the circulation control effect is enhanced accordingly.
As a further development of the invention, the bleed air source comes from an engine, and the loop control bleed air line draws high-pressure air from the engine.
As a further improvement of the invention, the engine is longitudinally arranged at the middle position of the fuselage between the left wing and the right wing, and the binary jet thrust vector device is arranged at the rear part of the nozzle of the engine.
As a further improvement of the invention, the binary jet thrust vectoring device comprises a thrust vectoring bleed air pipeline and a tail nozzle, wherein the tail nozzle is arranged at the rear part of an engine nozzle, and main flow sprayed out from the engine nozzle is sprayed out through the tail nozzle. The outlet end of the tail spray pipe is a rectangular nozzle with a rectangular cross section, the rectangular nozzle is connected with an outer expansion cover, the joint of the outer expansion cover and the rectangular nozzle forms an expansion step which expands outwards in four directions, namely an upper direction, a lower direction, a left direction and a right direction, and the upper side, the lower side, the left side and the right side of the outer expansion cover are outer expansion curved surfaces which expand outwards in the four directions, namely the upper direction, the lower direction, the left direction and the right direction respectively, so that an expansion nozzle of the binary jet thrust vector device is formed. The four inner side surfaces of the upper side surface, the lower side surface, the left side surface and the right side surface of the outer expanding cover are respectively provided with a thrust vector jet nozzle which is an upper thrust vector jet nozzle, a lower thrust vector jet nozzle, a left thrust vector jet nozzle and a right thrust vector jet nozzle. The included angle between the axial direction of the thrust vector jet nozzle and the normal direction of the expansion curved surface where the thrust vector jet nozzle is located is 75 degrees. The thrust vector air guide pipeline guides high-pressure air out of the engine, and the high-pressure air passes through the corresponding thrust vector electromagnetic valve and is ejected out of the corresponding thrust vector jet nozzle. When the thrust vector jet nozzle on any side works, the main stream in the tail nozzle can be pushed to the opposite side and attached to the outer expanding curved surface on the opposite side, and the main stream deflects to generate vector thrust. When the upper side thrust vector jet nozzle and the lower side thrust vector jet nozzle work, the binary jet thrust vector device provides pitching control moment. When the left thrust vector jet nozzle and the right thrust vector jet nozzle work, the binary jet thrust vector device provides yaw control moment. The expansion step can form a local low-pressure backflow area, so that the adhesion capability of the main flow to the outward-expanding curved surface is improved, the control capability of the main flow is enhanced, and the delay of the control process is reduced.
Compared with the prior art, the invention has the advantages that:
1) According to the invention, the synthetic jet actuator array is arranged on the front edge of the wing, under the excitation action of the synthetic jet, the flow separation of the leeward side of the wing is inhibited when the wing is at a low speed and at a large attack angle, and the flow is attached to the surface of the wing, so that the roll control effect of the circulation control actuator when the wing flies at a low speed and at a large attack angle can be improved.
2) The invention installs the adjustable nozzle ring volume control exciter at the rear edge of the outer side of the wing to provide rolling control for the aircraft. During high-subsonic-velocity flight, the coanda curved surface moves towards the air chamber under the traction of the piezoelectric contraction block to form a convergent-divergent type annular flow control nozzle, so that the wall attachment effect of supersonic jet flow is enhanced, and the influence of roll control failure on the robustness of a control system caused by the fact that the jet flow is separated from the coanda curved surface in the high-subsonic-velocity flight is avoided.
3) The invention utilizes the binary jet thrust vector device to control the pitching and the yawing in the wide-speed-range flight. During high subsonic flight, the incoming flow pressure is increased sharply, and the existing wing trailing edge circulation control device or the reverse jet device almost completely fails in pitch and yaw control. The pitch and yaw control of the binary jet thrust vector device is not affected by the outflow velocity. Meanwhile, the addition of the rear step strengthens the wall attachment effect of the main flow, enhances the control capability of the jet flow on the main flow and reduces the delay of the control process.
Therefore, compared with the prior art, the method ensures the reliability of the triaxial attitude control of the jet control aircraft during wide-speed-range and large-attack-angle flight. The invention can make the aircraft without control surface really realize high subsonic speed flight.
Drawings
FIG. 1 is a schematic view of the structure of the present invention;
FIG. 2 is a schematic view of the interior of the fuselage;
FIG. 3 is a schematic structural view (top view) of a synthetic jet actuator;
FIG. 4 is a schematic structural view (side view) of a synthetic jet actuator;
FIG. 5 is a schematic diagram of a synthetic jet actuator configuration;
fig. 6 is a schematic perspective view of the adjustable orifice ring volume control device.
FIG. 7 is a schematic structural diagram of an adjustable orifice circulation control device;
FIG. 8 is a schematic perspective view of a binary jet thrust vectoring device;
FIG. 9 is a schematic diagram of a binary jet thrust vectoring device;
reference numbers in the figures:
100. a body; 110. an engine nacelle; 120. a flow separation suppression device; 130. the adjustable nozzle circulation control device; 140. a binary jet thrust vector device; 150. a thrust vector bleed air line; 160. a loop control bleed line; 170. an engine;
121. a synthetic jet nozzle; 122. vibrating the diaphragm; 123. synthesizing a jet flow cavity; 124. a piezoelectric vibrator;
131. a volume control actuator housing; 132. controlling an upper air chamber by the loop quantity; 133. a lower air chamber is controlled by the circulation; 134. a piezoelectric shrinkage block; 135. the lower nozzle is controlled by the circulation; 136. the circulation control upper nozzle; 137. a coanda trailing edge;
141. a tail nozzle; 142. a thrust vector jet nozzle; 143. expanding the step outwards; 144. an outer expanding cover;
151. a thrust vector solenoid valve;
161. and a circulation control electromagnetic valve.
Detailed Description
For the purpose of promoting a clear understanding of the objects, aspects and advantages of the embodiments of the invention, reference will now be made to the drawings and detailed description, wherein there are shown in the drawings and described in detail, various modifications of the embodiments described herein, and other embodiments of the invention will be apparent to those skilled in the art. The exemplary embodiments of the present invention and the description thereof are provided to explain the present invention and not to limit the present invention.
Referring to fig. 1, an embodiment of the present invention provides a wide-speed-range jet control aircraft including a fuselage 100, an engine 170, and wings disposed on both left and right sides of the fuselage 100. The engine 170 is mounted in the nacelle 110 in a central position of the fuselage to power the aircraft.
A flow separation inhibiting device 120 is distributed on the front edge of each wing along the spanwise direction of the front edge of each wing and is used for inhibiting the flow separation on the surface of each wing;
the rear edge of the outer side of each wing is provided with an adjustable nozzle annular quantity control device 130 to provide rolling control for the aircraft;
a binary jet thrust vector device 140 is arranged in the middle of the rear end of the airplane body, and the binary jet thrust vector device 140 is used for pitch and yaw control in wide-speed-range flight.
A thrust vectoring bleed air line 150, a circulation control bleed air line 160 direct high pressure air from the engine to the binary jet thrust vectoring device 140 and the adjustable jet circulation control device 130, respectively.
Referring to fig. 2, the flow separation suppressing devices 120 are symmetrically distributed on the left and right wings. The flow separation suppression device 120 is comprised of a plurality of synthetic jet actuators. Each synthetic jet actuator is arranged in the wing, synthetic jet nozzles 121 of each synthetic jet actuator are uniformly arranged on the surface of the front edge of each wing along the spanwise direction of the wing, and gas is periodically blown out or sucked in through the synthetic jet nozzles 120 of each synthetic jet actuator, so that the flow separation of the surface of the wing is inhibited.
Referring to fig. 2, 3, 4 and 5, the synthetic jet actuator includes a synthetic jet cavity 123, a piezoelectric vibrator 124, a vibrating diaphragm 122 and a synthetic jet nozzle 121, the synthetic jet cavity 123 is a flat cylindrical cavity, the piezoelectric vibrator 124 is attached to the vibrating diaphragm 122, the vibrating diaphragm 122 serves as the upper surface of the synthetic jet cavity 123, the synthetic jet nozzle 121 is a slender slit, and the length direction of the synthetic jet nozzle 121 is consistent with the unfolding direction of the machine body; the synthetic jet nozzle 121 communicates with the synthetic jet cavity 123. Under the excitation of an electric signal, the piezoelectric vibrator 124 drives the vibrating diaphragm 122 to vibrate to change the volume of the synthetic jet cavity 123, so that the synthetic jet nozzle 121 periodically blows out or sucks in gas. Wherein the piezoelectric vibrator 124 is a piezoelectric ceramic or other electrically-excitable brake material.
When the aircraft flies at a low speed and a large attack angle, an electric signal is applied to the piezoelectric vibrator 124 for excitation, the piezoelectric vibrator 124 drives the vibrating diaphragm 122 to vibrate to change the volume of the synthetic jet cavity 123, and gas is periodically blown out or sucked in through the synthetic jet nozzle 121, so that the flow separation on the surface of the wing is inhibited, and the circulation control effect is improved.
Referring to fig. 1 and 2, the outer trailing edges of the left and right wings are respectively provided with an adjustable nozzle circulation control device 130, and the two adjustable nozzle circulation control devices 130 on the left and right wings are symmetrically distributed.
Referring to fig. 6 and 7, the adjustable orifice volume control device 130 employs an adjustable orifice volume control actuator. The adjustable nozzle ring amount control actuator comprises a ring amount control actuator shell 131, a ring amount control lower air chamber 133, a ring amount control upper air chamber 132, a piezoelectric contraction block 134, a ring amount control lower nozzle 135, a ring amount control upper nozzle 136 and a coanda trailing edge 137. The outer side rear edges of the left wing and the right wing are provided with notches for mounting the adjustable nozzle circulation control devices 130, the circulation control exciter shell 131 corresponds to the shape of the outer side rear edge notches of the wings, and the adjustable nozzle circulation control devices 130 are mounted in the notches corresponding to the outer side rear edges of the left wing and the right wing and are seamlessly connected with the wings to form a part of the wings, so that the aerodynamic shape of the aircraft is not influenced.
The interior of the housing 131 of the circulation control actuator is divided into two independent air chambers which are symmetrical up and down by a middle partition plate, namely an upper circulation control air chamber 132 and a lower circulation control air chamber 133, the front parts of the air chambers of the upper circulation control air chamber 132 and the lower circulation control air chamber 133 are respectively communicated with the circulation control bleed pipeline 160 through corresponding circulation control solenoid valves 161, and the high-pressure gas mass flow input into the upper circulation control air chamber 132 and the lower circulation control air chamber 133 is controlled through each circulation control solenoid valve 161. The circulation control bleed air line 160 is connected to a bleed air source, and introduces high-pressure air from the bleed air source into the circulation control upper air chamber 132 and the circulation control lower air chamber 133; the rear parts of the air chambers of the upper ring capacity control air chamber 132 and the lower ring capacity control air chamber 133 are respectively communicated with the corresponding upper ring capacity control nozzle and the lower ring capacity control nozzle, the end of the middle partition plate is connected with a coanda trailing edge 137, and the coanda trailing edge 137 is positioned between the upper ring capacity control nozzle 136 and the lower ring capacity control nozzle 135.
The bleed air source is from the engine 170 and the loop control bleed air line 136 draws high pressure air from the engine 170. The high-pressure gas passes through the circulation control bleed line 160, enters the circulation control upper air chamber 132 and the circulation control lower air chamber 133 through the circulation control solenoid valve 161, and is ejected from the circulation control upper nozzle 136 and the circulation control lower nozzle 135. Under the action of the flowing coanda effect, the jet flow is attached to the coanda trailing edge 137 to generate an entrainment effect on the flow of the boundary layer on the surface of the wing, so that the wing annular volume is changed, and further the lift force is changed. When the ring volume control upper nozzle 136 of the left wing trailing edge adjustable nozzle ring volume control exciter and the ring volume control lower nozzle 135 of the right wing trailing edge adjustable nozzle ring volume control exciter work, the left wing lift force is increased, the right wing lift force is reduced, and control torque for enabling the aircraft to roll rightwards is generated. On the contrary, when the circulation control upper nozzle 136 of the right wing trailing edge adjustable nozzle circulation control exciter and the circulation control lower nozzle 135 of the left wing trailing edge adjustable nozzle circulation control exciter work, the lift force of the right wing is increased, the lift force of the left wing is reduced, and control torque for enabling the aircraft to roll leftwards is generated.
Referring to fig. 7, the middle partition is a telescopic partition, the middle partition is provided with a piezoelectric expansion block 134, and the piezoelectric expansion block 134 is excited by an electric signal, so that the piezoelectric expansion block 134 contracts to drive the coanda trailing edge 137 to contract. When the piezoelectric telescopic block 134 is not excited by an electric signal, the coanda trailing edge 137 between the circulation control upper nozzle 136 and the circulation control lower nozzle 135 enables the circulation control upper nozzle 136 and the circulation control lower nozzle 135 to be both convergent nozzles. When the piezoelectric telescopic block 134 is excited by an electric signal, the piezoelectric telescopic block 134 contracts, and the coanda trailing edge 137 contracts, so that the circulation control upper nozzle 136 and the circulation control lower nozzle 135 are changed into a convergent-divergent nozzle. When the aircraft flies at a high subsonic speed, an electric signal is applied to the piezoelectric telescopic block 134 for excitation, the piezoelectric telescopic block 134 contracts, the coanda trailing edge 137 contracts, the annular quantity control upper nozzle 136 and the annular quantity control lower nozzle 135 are changed into convergent-divergent nozzles, airflow is changed into supersonic jet flow through the convergent-divergent nozzles, the jet flow is not easy to separate from the coanda trailing edge after the pressure of the air chamber is increased, the flowing wall attachment effect is enhanced, and the annular quantity control effect is enhanced accordingly.
Referring to fig. 1 and 2, the engine 170 is longitudinally disposed at the mid-fuselage location between the left and right wings, and the binary jet thrust vectoring device 140 is disposed aft of the engine nozzle.
Referring to fig. 8 and 9, the binary jet thrust vectoring device 140 includes a thrust vectoring bleed air line 150 and a tail nozzle 141, the tail nozzle 141 is disposed at the rear of an engine nozzle, and a main stream ejected from the engine nozzle is ejected through the tail nozzle 141. The outlet end of the tail nozzle 141 is a rectangular nozzle with a rectangular cross section, the rectangular nozzle is connected with an outer expanding cover 144, the joint of the outer expanding cover 144 and the rectangular nozzle forms an expanding step 143 which expands outwards in four directions, namely, up, down, left and right, and the four inner side surfaces of the outer expanding cover 144 are outer expanding curved surfaces which expand outwards in the directions of up, down, left and right respectively to form an expanding nozzle of the binary jet thrust vector device. Thrust vector jet nozzles 142 are arranged on the upper, lower, left and right inner side faces of the outer expanding cover 144 and are respectively an upper thrust vector jet nozzle, a lower thrust vector jet nozzle, a left thrust vector jet nozzle and a right thrust vector jet nozzle. The axial direction of the thrust vector jet nozzle 142 and the normal direction of the expansion curved surface where the thrust vector jet nozzle 142 is located form an included angle of 75 degrees. The thrust vector bleed air lines 150 draw high pressure air from the engine 170, which is emitted from the corresponding thrust vector jet nozzle 142 through the corresponding thrust vector solenoid valve 151. The high pressure gas mass flow in the thrust vector bleed line 150 is controlled by a thrust vector solenoid valve 151. When the thrust vector jet nozzle 142 on any side works, the main flow in the tail nozzle 141 can be pushed to the opposite side and attached to the outer expanding curved surface of the opposite side, and the main flow deflects to generate vector thrust. When the upper thrust vector jet nozzle is in operation, the binary jet thrust vector device 140 provides a head-up control torque. The binary jet thrust vectoring device 140 provides a low head control torque when the lower thrust vectoring jet nozzle is in operation. When the left thrust vector jet nozzle works, the binary jet thrust vector 140 device provides a left yaw control moment. When the right thrust vector jet nozzle works, the binary jet thrust vector 140 device provides a right yaw control moment. When the upper side thrust vector jet nozzle and the lower side thrust vector jet nozzle work, the binary jet thrust vector device provides pitching control moment. When the left thrust vector jet nozzle and the right thrust vector jet nozzle work, the binary jet thrust vector device provides yaw control moment.
The expansion step 143 can form a local low-pressure backflow area, so that the adhesion capability of the main flow to the outer expansion curved surface is improved, the control capability of the main flow is enhanced, and the delay of the pitching and yawing control processes is reduced.
The above-mentioned embodiments only express several embodiments of the present application, and the description thereof is specific and detailed, but not to be understood as limiting the scope of the invention. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the concept of the present application, which falls within the scope of protection of the present application. Therefore, the protection scope of the present patent application shall be subject to the appended claims.
Claims (15)
1. The jet flow control aircraft with the wide speed range is characterized by comprising an aircraft body and wings arranged on the left side and the right side of the aircraft body;
flow separation inhibiting devices are distributed on the front edge of each wing along the spanwise direction of the wing, and are used for inhibiting flow separation on the surface of the wing;
the rear edge of the outer side of each wing is provided with an adjustable nozzle circulation control device to provide rolling control for the aircraft;
a binary jet thrust vector device is arranged in the middle of the rear end of the airplane body, and the binary jet thrust vector device is used for pitch and yaw control in wide-speed-range flight;
the engine is longitudinally arranged in the middle of the fuselage between the left wing and the right wing, and the binary jet thrust vector device is arranged at the rear part of the nozzle of the engine;
the binary jet thrust vectoring device comprises a thrust vectoring bleed air pipeline and a tail spray pipe, the tail spray pipe is arranged at the rear part of an engine nozzle, and main flow sprayed out from the engine nozzle is sprayed out through the tail spray pipe; the outlet end of the tail spray pipe is a rectangular nozzle with a rectangular section, the rectangular nozzle is connected with an external expansion cover, expansion steps which expand outwards in four directions, namely the upper direction, the lower direction, the left direction and the right direction, are formed at the joint of the external expansion cover and the rectangular nozzle, and the upper inner side surface, the lower inner side surface, the left inner side surface and the right inner side surface of the external expansion cover are external expansion curved surfaces which expand outwards in the upper direction, the lower direction, the left direction and the right direction respectively to form an expansion type nozzle of the binary jet thrust vector device; the four inner side surfaces of the upper side surface, the lower side surface, the left side surface and the right side surface of the outer expanding cover are respectively provided with a thrust vector jet nozzle which is an upper thrust vector jet nozzle, a lower thrust vector jet nozzle, a left thrust vector jet nozzle and a right thrust vector jet nozzle.
2. The wide velocity region jet control aircraft of claim 1, wherein the flow separation suppression devices on the left and right airfoils are distributed symmetrically left and right.
3. The wide-speed-range jet control aircraft according to claim 2, wherein the flow separation suppression device comprises a plurality of synthetic jet actuators, each synthetic jet actuator is arranged in the airfoil, synthetic jet nozzles of each synthetic jet actuator are uniformly arranged on the surface of the leading edge of each airfoil along the span direction of the leading edge, and the synthetic jet nozzles of each synthetic jet actuator periodically blow out or suck in gas so as to suppress flow separation on the surface of the airfoil.
4. The wide-speed-range jet control aircraft according to claim 3, wherein the synthetic jet actuator comprises a synthetic jet cavity, a piezoelectric vibrator, a vibrating diaphragm and a synthetic jet nozzle, the piezoelectric vibrator is attached to the vibrating diaphragm, the vibrating diaphragm serves as the upper surface of the synthetic jet cavity, the synthetic jet nozzle is a long and thin slit, and the length direction of the synthetic jet nozzle is consistent with the unfolding direction of the aircraft body; the synthetic jet nozzle is communicated with the synthetic jet cavity; under the excitation of an electric signal, the piezoelectric vibrator drives the vibrating diaphragm to vibrate to change the volume of the synthetic jet cavity, so that the synthetic jet nozzle periodically blows out or sucks in gas.
5. The wide velocity range jet control aircraft of any one of claims 1 to 4, wherein the outer trailing edges of the left wing and the right wing are respectively provided with an adjustable nozzle circulation control device, and the two adjustable nozzle circulation control devices on the left wing and the right wing are distributed in bilateral symmetry.
6. The wide velocity range jet control aircraft of claim 5, wherein the adjustable nozzle circulation control device is an adjustable nozzle circulation control actuator, the adjustable nozzle circulation control actuator comprises an circulation control actuator housing, the outer trailing edges of the left and right wings are provided with notches for mounting the adjustable nozzle circulation control device, the circulation control actuator housing corresponds to the shape of the notch of the outer trailing edge of the wing, and the adjustable nozzle circulation control device is mounted in the notches corresponding to the outer trailing edges of the left and right wings and is seamlessly connected with the wing to form a part of the wing.
7. The wide velocity range jet control aircraft according to claim 6, wherein the interior of the circular control actuator housing is divided into two independent air chambers which are symmetrical up and down by a middle partition plate, the two independent air chambers are respectively a circular control upper air chamber and a circular control lower air chamber, the front parts of the air chambers of the circular control upper air chamber and the circular control lower air chamber are respectively communicated with the corresponding circular control air-introducing pipelines through the corresponding circular control electromagnetic valves, the circular control air-introducing pipelines are connected with an air-introducing source, and high-pressure air from the air-introducing source is introduced into the circular control upper air chamber and the circular control lower air chamber; the rear parts of the air chambers of the upper circulation control air chamber and the lower circulation control air chamber are respectively communicated with the corresponding upper circulation control nozzle and the lower circulation control nozzle, the end of the middle partition plate is connected with a coanda trailing edge, and the coanda trailing edge is positioned between the upper circulation control nozzle and the lower circulation control nozzle.
8. The wide-speed-range jet control aircraft according to claim 7, wherein when the circulation control upper nozzle of the left wing trailing edge adjustable nozzle circulation control actuator and the circulation control lower nozzle of the right wing trailing edge adjustable nozzle circulation control actuator work, the lift force of the left wing is increased, the lift force of the right wing is reduced, and a control moment for rolling the aircraft to the right is generated; on the contrary, when the upper annular volume control nozzle of the right wing trailing edge adjustable nozzle annular volume control exciter and the lower annular volume control nozzle of the left wing trailing edge adjustable nozzle annular volume control exciter work, the lift force of the right wing is increased, the lift force of the left wing is reduced, and control torque for enabling the aircraft to roll leftwards is generated.
9. The wide velocity range jet control aircraft of claim 7, wherein the intermediate diaphragm is a retractable diaphragm, the intermediate diaphragm is provided with a piezoelectric telescopic block, the piezoelectric telescopic block is excited by an electric signal, and the piezoelectric telescopic block contracts to drive the coanda trailing edge to contract.
10. The wide velocity range jet control aircraft of claim 9, wherein when the piezoelectric telescopic blocks are not excited by electrical signals, the coanda trailing edge between the circulation control upper nozzle and the circulation control lower nozzle enables both the circulation control upper nozzle and the circulation control lower nozzle to be convergent nozzles; when the piezoelectric telescopic block is excited by applying an electric signal, the piezoelectric telescopic block contracts, the coanda trailing edge contracts, and the annular quantity control upper nozzle and the annular quantity control lower nozzle are changed into a convergent divergent nozzle.
11. The wide-speed-range jet control aircraft according to claim 10, wherein when the aircraft flies at high subsonic speed, an electric signal is applied to the piezoelectric telescopic block for excitation, airflow passes through the convergent-divergent nozzle to be changed into supersonic jet, the jet is not easy to separate from a coanda trailing edge after the pressure of the air chamber is increased, the flowing coanda effect is enhanced, and the annular volume control effect is enhanced accordingly.
12. The wide velocity region jet control aircraft of any one of claims 7 to 11, wherein the bleed air source is from an engine and the loop control bleed air line draws high pressure air from the engine.
13. The wide velocity range jet control aircraft of claim 1, wherein the thrust vector jet nozzle axis direction is 75 ° from the normal direction of the expansion surface on which the thrust vector jet nozzle is located.
14. The wide velocity region jet control aircraft of claim 1, wherein the thrust vector bleed line draws high pressure gas from the engine, the high pressure gas being ejected from the corresponding thrust vector jet nozzle through the corresponding thrust vector solenoid valve; when the thrust vector jet nozzle on any side works, the main stream in the tail nozzle is pushed to the opposite side and is attached to the outer expanding curved surface on the opposite side, and the main stream deflects to generate vector thrust.
15. The wide velocity region jet control aircraft of claim 14, wherein the binary jet thrust vectoring device provides a pitch control torque when the upper and lower thrust vectoring jet nozzles are operational; when the left thrust vector jet nozzle and the right thrust vector jet nozzle work, the binary jet thrust vector device provides yaw control moment.
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| CN113830291B (en) * | 2021-11-05 | 2024-01-16 | 中国人民解放军国防科技大学 | Virtual variable pneumatic layout intelligent control system of aircraft |
| CN114056551B (en) * | 2022-01-12 | 2022-04-01 | 中国空气动力研究与发展中心低速空气动力研究所 | Virtual wing belly flap and wing body fusion airplane, constant air blowing method and variable-angle air blowing method |
| CN114291252B (en) * | 2022-01-27 | 2024-02-27 | 北京航空航天大学 | Three-axis attitude control system and method for aircraft |
| CN114684353B (en) * | 2022-06-02 | 2022-10-14 | 中国空气动力研究与发展中心低速空气动力研究所 | Pulse jet actuator, wing and aircraft |
| CN115092414B (en) * | 2022-07-05 | 2024-02-02 | 中国人民解放军国防科技大学 | Annular quantity control airfoil pneumatic and electromagnetic stealth combined optimization method |
| CN115339617B (en) * | 2022-10-18 | 2023-01-24 | 中国空气动力研究与发展中心低速空气动力研究所 | Jet flow control mechanism, jet flow control system, jet flow control method and flight equipment |
| CN115892470B (en) * | 2023-01-09 | 2023-05-23 | 中国空气动力研究与发展中心高速空气动力研究所 | Built-in equipment separation safety protection system |
| CN116923688B (en) * | 2023-09-15 | 2023-12-08 | 中国空气动力研究与发展中心低速空气动力研究所 | Jet flow circulation control device |
| CN117087865B (en) * | 2023-10-20 | 2024-01-26 | 中国空气动力研究与发展中心计算空气动力研究所 | Flying wing pneumatic aircraft and control method |
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| US7861977B1 (en) * | 2006-03-13 | 2011-01-04 | The United States Of America As Represented By The Secretary Of The Navy | Adaptive material actuators for Coanda effect circulation control slots |
| CN102991669B (en) * | 2012-12-12 | 2014-12-03 | 北京理工大学 | Aircraft fluidic thrust vector control system |
| US10005544B2 (en) * | 2015-04-18 | 2018-06-26 | The Boeing Company | System and method for enhancing the high-lift performance of an aircraft |
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