CN117227987B - Unilateral expansion tail spray groove integrally designed with control surface - Google Patents
Unilateral expansion tail spray groove integrally designed with control surface Download PDFInfo
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- CN117227987B CN117227987B CN202311509785.0A CN202311509785A CN117227987B CN 117227987 B CN117227987 B CN 117227987B CN 202311509785 A CN202311509785 A CN 202311509785A CN 117227987 B CN117227987 B CN 117227987B
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- 239000007921 spray Substances 0.000 title claims abstract description 58
- 238000013461 design Methods 0.000 claims abstract description 20
- 230000008859 change Effects 0.000 claims abstract description 9
- 238000002347 injection Methods 0.000 claims description 20
- 239000007924 injection Substances 0.000 claims description 20
- 230000005855 radiation Effects 0.000 abstract description 13
- 230000000694 effects Effects 0.000 description 5
- 238000005507 spraying Methods 0.000 description 4
- 238000011161 development Methods 0.000 description 3
- 230000018109 developmental process Effects 0.000 description 3
- 238000002156 mixing Methods 0.000 description 3
- 238000001816 cooling Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000001276 controlling effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 230000004927 fusion Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 230000001629 suppression Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Abstract
The application discloses a unilateral expansion tail spray groove integrally designed with a control surface, and relates to the technical field of aircraft design; the unilateral expansion tail jet slot integrated with the control surface is provided with a tail jet slot at the tail part of the machine body, the machine body is hinged with an elevator, the upper side of the machine body is provided with a tail jet slot communicated with the tail jet slot, tail jet flow is discharged through the tail jet slot by the tail jet slot, tail jet flow is shielded by the elevator, and the tail jet slot on the elevator rotates along with the elevator to change the direction of the tail jet flow in the pitching direction. The unilateral expansion tail spray groove integrated with the control surface can not only shield infrared radiation of tail spray, but also provide vector thrust, thereby meeting the requirements of low infrared radiation and vector thrust.
Description
Technical Field
The application relates to the technical field of aircraft design, in particular to a unilateral expansion tail spray groove integrated with a control surface.
Background
Mobility and stealth are performance metrics that must be considered for future advanced fighter designs. As an important component of fighter plane design, the advances in powered aircraft engines are not only reflected in high thrust-to-weight ratios, but also in infrared stealth capability and vector thrust. The development of infrared stealth technology is a key for improving the survivability of fighter plane, and the control and development of vector thrust provide excellent maneuvering flight capability for fighter plane. The key component that is most inseparable from these two technological developments is the engine exhaust nozzle.
Axisymmetric nozzles are commonly used in conventional aircraft engines. An axisymmetric nozzle is the most widely used and mature nozzle with good internal flow characteristics, and can be designed to perform 20-degree vector adjustment within 360 degrees of the circumferential direction, but the corresponding adjusting structure not only increases the complexity of the system, but also increases the total weight of the nozzle. Moreover, due to the structural limitations of axisymmetric nozzles, the interior cavity thereof does not have good infrared suppression capability. Furthermore, since the axisymmetric nozzle is cylindrical in shape, it is not well compatible with the aircraft aft body, which results in significant aft body drag.
Disclosure of Invention
The purpose of this application is to provide a unilateral inflation tail spouts groove with control surface integrated design, not only can shelter from tail jet infrared radiation, can also provide vector thrust, has satisfied low infrared radiation and has provided the requirement of vector thrust.
In order to achieve the above purpose, the application provides a unilateral expansion tail spouts groove with control surface integrated design, has seted up the tail spout at the afterbody of fuselage, the fuselage articulates there is the elevator the upside of fuselage seted up with the tail spouts groove of tail spout intercommunication, through the tail spout warp the tail spouts the groove and discharges the tail jet, through the elevator shelters from the tail jet, just tail spouts the groove on the elevator with the direction of tail jet is changed in the every single move direction along with the elevator rotation.
In some embodiments, a tail jet injection groove is formed in the surface of the tail jet groove on the elevator, and the tail jet injection groove is communicated with the tail jet groove upwards and communicated with the atmosphere downwards.
In some embodiments, the tail jet slots are equally spaced on the tail jet slots.
In some embodiments, a tail spray slot upper web hinged to the fuselage is provided above the tail spray slot, and the geometric vector angle of the tail spray slot is changed by rotation of the tail spray slot upper web.
In some embodiments, the rotation range of the web on the tail spray slot is-5 DEG to 5 deg.
In some embodiments, the shape of the web on the tail spout is inverted triangle.
In some embodiments, the tail spray slot and the elevator rotate in a range of-30 ° to 30 °.
In some embodiments, the elevator is further hinged with a tab.
In some embodiments, the rear body portion of the fuselage, elevator and adjustment tab together is inverted triangular in shape.
In some embodiments, the tail nozzle and the tail nozzle slot are arranged in pairs and symmetrically distributed on two sides of one side of the tail of the machine body.
Compared with the background art, the unilateral expansion tail jet slot integrally designed with the control surface is provided, the tail jet slot is formed in the tail of the machine body, the machine body is hinged with the elevator, the tail jet slot communicated with the tail jet slot is formed in the upper side of the machine body, the tail jet is discharged through the tail jet slot and is shielded through the elevator, and the tail jet slot on the elevator rotates along with the elevator to change the direction of the tail jet in the pitching direction.
The scheme provides a novel integrated spray pipe design mode, and meets the requirements of low infrared radiation and vector thrust provision for meeting the maneuvering performance. The tail jet slot of integrated design can be well integrated with the rear body of the aircraft, and the surface of the rear body of the aircraft is used as a part of expansion surface of the rear body of the aircraft, so that the weight of the tail jet slot can be greatly reduced, and the rear body resistance of the aircraft is reduced. The longer expansion surface can block the infrared radiation of the hot jet flow in certain important directions. The integral tail jet slot rotates along with the elevator within a certain range, so that the expansion section of the jet pipe can be adjusted to adapt to the change of the state of the engine, and vector thrust can be provided. Vector adjustment in this manner not only reduces the structural complexity, but also reduces the weight relative to axisymmetric nozzles. The scheme effectively solves the problem of pitch control of the tailless/flying wing layout aircraft during low/sub/span/supersonic cruising or maneuvering flight.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings that are required to be used in the embodiments or the description of the prior art will be briefly described below, and it is obvious that the drawings in the following description are only embodiments of the present application, and that other drawings may be obtained according to the provided drawings without inventive effort to a person skilled in the art.
FIG. 1 is a schematic structural diagram of a single-side expansion tail spray tank integrally designed with a control surface according to an embodiment of the present disclosure;
FIG. 2 is a top view of a single-sided expansion tail jet slot integrally designed with a control surface according to an embodiment of the present disclosure;
fig. 3 is a side view of a single-sided expansion tail spray slot integrally designed with a control surface according to an embodiment of the present application.
Wherein:
the device comprises a 1-machine body, a 2-tail nozzle, a web rotation axis on a 3-tail spray tank, a web on a 4-tail spray tank, a 5-tail spray injection tank, a 6-elevator rotation axis, a 7-tail spray tank, an 8-elevator, a 9-adjusting plate rotation axis and a 10-adjusting plate.
Detailed Description
The following description of the embodiments of the present application will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all, of the embodiments of the present application. All other embodiments, which can be made by one of ordinary skill in the art without undue burden from the present disclosure, are within the scope of the present disclosure.
In order to better understand the aspects of the present application, a further detailed description of the present application will be provided below with reference to the accompanying drawings and detailed description.
Please refer to fig. 1 to 3, wherein fig. 1 is a schematic structural diagram of a single-side expansion tail spray groove integrally designed with a control surface provided in an embodiment of the present application, fig. 2 is a top view of a single-side expansion tail spray groove integrally designed with a control surface provided in an embodiment of the present application, and fig. 3 is a side view of a single-side expansion tail spray groove integrally designed with a control surface provided in an embodiment of the present application.
Aiming at the prior art, the integrated design of the airplane body and the spray pipe/back body is particularly important for improving the lateral and backward stealth performance of the airplane. The integrated design of the jet pipe/the rear body ensures that the plane ridge better meets the parallel principle, effectively reduces the radar scattering area, and on the other hand, the jet pipe of the engine is required to strengthen the cooling mixing of jet flow and outflow, plays a certain shielding role and effectively weakens infrared radiation.
Based on the design, the application provides a unilateral expansion tail spray groove design scheme integrated with a control surface, belongs to the technical field of aviation aircraft design, relates to the technical research field of aviation aircraft pitching control, and particularly relates to an engine tail spray pipe design for effectively improving pitching control capability and considering pneumatic infrared stealth characteristics when a tailless/flying wing layout aircraft cruises or maneuvers at low/sub/span/supersonic speed.
The scheme specifically comprises the following steps: the tail nozzle 2 is arranged at the tail part of the machine body 1, the machine body 1 is hinged with an elevator 8, and a tail nozzle groove 7 communicated with the tail nozzle 2 is arranged at the upper side of the elevator 8.
In the present embodiment, the tail jet is discharged through the tail jet slot 7 through the tail jet nozzle 2; the elevator 8 shields the high Wen Wei jet flow and has the stealth function of infrared shielding below; when the elevator 8 rotates, the tail jet groove 7 rotates together with it, and changes the direction of the tail jet in the pitch direction.
The scheme provides a novel integrated spray pipe design mode, and meets the requirements of low infrared radiation and vector thrust provision for meeting the maneuvering performance. The tail jet slot 7 of integrated design can be well integrated with the rear body of the aircraft, and the surface of the rear body of the aircraft is used as a part of expansion surface of the rear body of the aircraft, so that the weight of the tail jet slot can be greatly reduced, and the rear body resistance of the aircraft is reduced. The longer expansion surface can block the infrared radiation of the hot jet flow in certain important directions. And the integral tail jet slot 7 rotates along with the elevator 8 in a certain range, so that the expansion section size of the jet pipe can be adjusted to adapt to the change of the state of the engine, and vector thrust can be provided. Vector adjustment in this manner not only reduces the structural complexity, but also reduces the weight relative to axisymmetric nozzles. The scheme effectively solves the problem of pitch control of the tailless/flying wing layout aircraft during low/sub/span/supersonic cruising or maneuvering flight.
Furthermore, the aviation aircraft can be changed based on the scheme, so that the changed aviation aircraft can effectively take the characteristics of stealth and vector thrust into consideration, and the problem of design contradiction between high stealth performance and high aerodynamic performance is solved; the infrared characteristics of the aircraft are effectively reduced, the vector thrust index is realized, the long-range capability, the survivability and the quick response capability of the aircraft are improved, and the low/sub/span/supersonic cruising and high maneuver flight are realized.
In some embodiments, the range of rotation of the tail boom 7 and elevator 8 is-30 deg..
In the embodiment, the range of the vertical deflection angle of the expansion edge of the tail spray groove 7 is-30 degrees to 30 degrees, and the expansion edge is consistent with the elevator 8, so that two functions are realized: the tail jet groove 7 is arranged on the leeward side of the elevator 8, plays a role in shielding high-temperature tail jet, weakens the radiation of infrared rays of the tail jet to the lower part, and improves the stealth performance of the lower part; secondly, the deflection of the elevator 8 directly influences the flow direction of tail jet flow, so that the direction of a thrust line is changed, the effect of a thrust vector is achieved, and the pitching control capability is further improved.
In some embodiments, a tail jet injection groove 5 is formed on the surface of a tail jet groove 7 on an elevator 8, the tail jet injection groove 5 is communicated with the tail jet groove 7 upwards and downwards and communicated with the atmosphere, the tail jet injection groove 5 formed on the expansion edge of the tail jet groove 7 is used for injecting jet flow to adjust the tail jet flow pneumatic boundary, and the infrared radiation intensity is reduced through cold and hot flow blending.
Specifically, in this embodiment, the slot of the tail jet injection slot 5 is communicated with the atmosphere, so as to realize two functions: under the condition of different engine drop pressure ratios, jet flow generated by the tail jet injection groove 5 is different, the expansion pneumatic boundary under the jet pipe is different, and the micro change of jet flow of the engine is realized; and secondly, the air cooling air introduced through the tail jet injection groove 5 is mixed with tail jet, namely hot exhaust tail flame, so that the temperature of the tail flame can be effectively reduced, and the infrared characteristic of the jet of the engine is reduced.
Illustratively, the tail jet slots 5 are equally spaced on the tail jet slot 7.
In the embodiment, three tail spray injection grooves 5 are formed in the unilateral expansion part of the tail spray groove 7 at equal intervals, the three tail spray injection grooves 5 deflect together with the tail spray groove 7, and the pneumatic boundary adjustment of tail spray flows and the mixing of cold and hot air flows are realized through different jet flow amounts.
In some embodiments, a tail slot upper web 4 hinged to the fuselage 1 is provided above the tail slot 7, and the geometric vector angle of the tail slot 7 is changed by rotation of the tail slot upper web 4.
In the embodiment, the root of the upper web 4 of the tail spray groove is connected with the machine body 1 by adopting a hinge and rotates around the rotation axis 3 of the upper web of the tail spray groove; the upper web 4 of the tail jet slot forms different thrust vector angles through being matched with the elevator 8 to deflect, so that the geometric vector angle of the expansion channel of the tail jet pipe can be effectively changed, small gesture changes after the large change of pitching gestures are controlled under the large rudder effect of the elevator 8 are compensated, and the capability of controlling the large gesture and the small gesture is realized.
The rotation range of the web 4 on the tail spray groove is-5 degrees, and the angle deflection of-5 degrees up and down is realized; the shape of the upper web 4 of the tail spray groove is an inverted triangle, and the sharp corner of the triangle faces away from the side of the machine body 1 and faces the side of the elevator 8.
In addition to this, the elevator 8 is also articulated with a regulating plate 10.
In this embodiment, the rear body portion formed by the main body 1, the elevator 8 and the adjusting plate 10 is in an inverted triangle shape, and the leeward side is provided with a semi-expansion type tail nozzle 2 and a tail nozzle groove 7. The expansion edge on the lower surface of the tail jet slot 7 divides an inverted triangle area with the tail jet slot 7 into two parts at a certain distance from the tail jet slot 2, the part of the tail jet slot 2 is a fixed part, the inverted triangle part is a movable part, and the movable part is an elevator 8. And a sufficient gap required by deflection is reserved between the fixed part and the elevator 8, and meanwhile, a curved auxiliary surface which is tangentially connected with the control surface of the elevator 8 is generated at the dividing position and extends into the elevator to fill a large gap reserved between the elevator 8 and the fixed part after deflection.
It should be noted that all hinges mentioned in this application may be implemented as specific embodiments.
In a specific embodiment, the components related to the single-side expansion tail spray groove comprise a machine body 1, a tail nozzle 2, a web rotation axis 3 on the tail spray groove, a web 4 on the tail spray groove, a tail spray injection groove 5, an elevator rotation axis 6, a tail spray groove 7 and an elevator 8.
The elevator 8, the machine body 1 and the tail nozzle 2 are in fusion transition in appearance, and no obvious step exists. The tail nozzle 2 and the tail spraying groove 7 are positioned on the leeward surfaces of the machine body 1 and the elevator 8, the tail nozzle 2 and the tail spraying groove 7 are arranged in pairs, and are symmetrically distributed on two sides of one side of the tail of the machine body 1, and the infrared stealth performance to the lower side is improved by means of the shielding effect of the machine body 1 and the elevator 8.
The tail spraying groove 7 is located at 82.7-94% of the rear body of the machine body 1, and a fixed part and a movable part are divided at 89.9% of the machine body 1, wherein the fixed part is the machine body 1 and the tail nozzle 2, and the movable part is the tail spraying groove 7. The movable part rotates with the elevator 8 about the elevator rotation axis 6 and leaves a space gap with the fuselage 1 required for deflection, extending the cutting surface near the side of the fuselage 1 in the form of an arc-shaped surface for a distance inside the fuselage 1, as shown in fig. 3.
The upper web 4 of the tail spray groove is located at 82.7-83.2% of the rear body of the machine body 1, and is in an inverted triangle shape, the upper web 4 of the tail spray groove is tightly matched with the machine body 1 by adopting a round front edge, the rotation axis 3 of the upper web of the tail spray groove is a circle center connecting line of the front edge of the upper web 4 of the tail spray groove, and the change of the geometrical vector angle of the outlet of the spray pipe is realized around the rotation axis 3 of the upper web of the tail spray groove, so that the small posture change of the pitching direction is controlled.
The tail jet injection grooves 5 are positioned between 85.1% and 87.2% of the rear body of the machine body 1, the three tail jet injection grooves 5 are distributed at equal intervals, the distance is 250mm, the flow direction width of the tail jet injection grooves 5 is 50mm, and the included angle between the central line of the tail jet injection grooves 5 and the horizontal line is 30 degrees.
In summary, in the scheme of the unilateral expansion tail spray groove integrally designed with the control surface, the tail spray groove 7 is highly fused with the tail part of the machine body 1 and the elevator 8 and is arranged on the leeward surface of the elevator 8, so that the infrared radiation below the elevator 8 can be shielded by the high Wen Wei jet flow, the infrared stealth performance below the elevator is improved, and the rudder control efficiency of the elevator 8 can be improved by means of the injection effect of the tail jet flow; the deflected elevator 8 is equivalent to a rotary tail nozzle with a mechanical thrust vector, so that the jet direction of the tail jet can be effectively changed, and the thrust line is changed, and the thrust vector effect is realized; the tail jet injection groove 5 is formed in the expansion edge of the tail jet pipe, so that the adjustment of the pneumatic boundary of the tail jet flow and the reduction of the infrared radiation intensity are realized. The scheme can be applied to pneumatic layout design of various tailless/flying wing layout aircrafts.
It should be noted that many of the components mentioned in this application are common standard components or components known to those skilled in the art, and the structures and principles thereof are known to those skilled in the art from technical manuals or by routine experimental methods.
It should be noted that in this specification relational terms such as first and second are used solely to distinguish one entity from another entity without necessarily requiring or implying any actual such relationship or order between such entities.
The single-side expansion tail spray groove integrally designed with the control surface is provided by the application and is described in detail above. Specific examples are set forth herein to illustrate the principles and embodiments of the present application, and the description of the examples above is only intended to assist in understanding the methods of the present application and their core ideas. It should be noted that it would be obvious to those skilled in the art that various improvements and modifications can be made to the present application without departing from the principles of the present application, and such improvements and modifications fall within the scope of the claims of the present application.
Claims (10)
1. The utility model provides a unilateral expansion tail spouts groove with control surface integrated design, its characterized in that, the afterbody of fuselage (1) articulates has elevator (8), has seted up tail spout (2) at the afterbody of fuselage (1) the upside of fuselage (1) afterbody and tail spouts groove (7) that are seted up on elevator (8) with tail spout (2) intercommunication, through tail spout (2) warp tail spouts groove (7) discharge tail spouts, through elevator (8) shelter from tail spouts, tail spouts groove (7) on elevator (8) with the upper and lower deflection angle of elevator (8) is unanimous, tail spouts groove (7) on elevator (8) are along with elevator (8) are together rotated in order to change the direction of tail spouts in the every single move direction.
2. The unilateral expansion tail spray groove integrally designed with the control surface according to claim 1, wherein a tail spray injection groove (5) is formed on the surface of a tail spray groove (7) on the elevator (8), and the tail spray injection groove (5) is communicated with the tail spray groove (7) upwards and communicated with the atmosphere downwards.
3. The single-sided expansion tail jet slot integrally designed with the control surface according to claim 2, wherein the tail jet slots (5) are distributed on the tail jet slot (7) at equal intervals.
4. Single-sided expansion tail jet slot designed in an integrated manner with a control surface according to claim 1, characterized in that a tail jet slot upper web (4) hinged to the fuselage (1) is arranged above the tail jet slot (7), the geometrical vector angle of the tail jet slot (7) being changed by the rotation of the tail jet slot upper web (4).
5. The single-sided expansion tail jet slot integrally designed with the control surface as claimed in claim 4, wherein the rotation range of the web (4) on the tail jet slot is-5 °.
6. The single-sided expansion tail jet slot of integrated design with a control surface as claimed in claim 4, characterized in that the shape of the upper web (4) of the tail jet slot is inverted triangle.
7. The single-sided expansion tail jet slot integrally designed with a control surface according to claim 1, characterized in that the rotation range of the tail jet slot (7) and the elevator (8) is-30 °.
8. Single-sided expansion tail jet slot designed integrally with a control surface according to claim 1, characterized in that the elevator (8) is also hinged with an adjusting piece (10).
9. The single-sided expansion tail jet slot designed integrally with a control surface according to claim 8, characterized in that the shape of the rear body part which is composed of the fuselage (1), the elevator (8) and the adjusting piece (10) together is an inverted triangle.
10. The single-side expansion tail spray groove integrally designed with the control surface according to claim 1, wherein the tail spray nozzles (2) and the tail spray groove (7) are arranged in pairs and symmetrically distributed on two sides of one side of the tail of the machine body (1).
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| CN202311509785.0A CN117227987B (en) | 2023-11-14 | 2023-11-14 | Unilateral expansion tail spray groove integrally designed with control surface |
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| CN202311509785.0A CN117227987B (en) | 2023-11-14 | 2023-11-14 | Unilateral expansion tail spray groove integrally designed with control surface |
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| CN117227987B true CN117227987B (en) | 2024-03-12 |
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