CN114104254A - Pneumatic appearance structure of supersonic speed large maneuvering target - Google Patents
Pneumatic appearance structure of supersonic speed large maneuvering target Download PDFInfo
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- CN114104254A CN114104254A CN202111317850.0A CN202111317850A CN114104254A CN 114104254 A CN114104254 A CN 114104254A CN 202111317850 A CN202111317850 A CN 202111317850A CN 114104254 A CN114104254 A CN 114104254A
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- supersonic
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
- B64C3/14—Aerofoil profile
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/10—All-wing aircraft
- B64C2039/105—All-wing aircraft of blended wing body type
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention provides a pneumatic appearance of a supersonic speed large-maneuvering target, wherein a hood is molded by Von Karman curve lofting; the two duck wings are respectively arranged at two ends of the head cover, and the duck wings adopt trapezoidal wings with medium sweepback angles; the middle-rear section of the bullet body is positioned at the rear end of the head cover and adopts a straight section with a circular cross section; the two missile wings are respectively arranged on two sides of the middle rear section of the missile body; the interstage transition cabin is connected with the task stage and the booster in series; the booster body is positioned at the rear end of the interstage transition cabin and adopts a straight section with a circular cross section; the number of the rotary tail wings is four, and the rotary tail wings are arranged at the tail part of the booster body; the two ailerons are respectively arranged at two sides of the back section of the missile body and are positioned at the back edge end of the missile wing; the vertical tail is a swallow-shaped vertical tail and is respectively arranged at two ends of the wing tip of the missile wing. The appearance can make the target realize wide speed range flight, and the target of this aerodynamic appearance is excellent at the aerodynamic performance of big maneuver flight of supersonic speed simultaneously, and the handling performance is good, has filled the blank in big maneuver target field of supersonic speed, can satisfy the demand of novel weapon appraisal and war standard.
Description
Technical Field
The invention relates to the technical field of pneumatic appearance design of targets, in particular to a pneumatic appearance of a supersonic speed large-motor target.
Background
In recent years, with the rapid development of the four-five generation fighters in various countries, a great threat is formed to national defense safety in China, so that the development of a target simulating a new generation fighter becomes an important task for novel weapon identification and daily combat training of troops. The supersonic speed large maneuvering flight is the most prominent flight characteristic of the new generation of fighters and also becomes the key point of the target needing simulation. The existing train targets in China mainly focus on low-speed and high subsonic flight ranges, the existing supersonic speed targets are only limited to achieve supersonic cruise flight, and targets capable of simulating supersonic speed large-maneuvering flight capability of a five-generation aircraft still fall into the blank.
Disclosure of Invention
The invention provides a target aerodynamic profile for realizing supersonic speed large maneuvering flight capability at home for the first time. The target adopts a ground boosting launching mode, and a mission stage and a booster are connected in series through an interstage transition cabin. The pneumatic appearance target can realize supersonic speed large-maneuvering flight under a large airspace (8-14 km), a wide speed area (0.8-1.6 Ma) and a large-maneuvering (stable 6g flight, instantaneous 9g flight) wide flight envelope.
In order to achieve the above object, the pneumatic profile of the target of the present invention comprises:
the hood line is molded by adopting Von Karman curve lofting;
the middle and rear section of the bullet body is positioned at the rear end of the head cover and adopts a straight section with a circular cross section;
the two duck wings are respectively arranged at two ends of the head cover and adopt trapezoidal wings with medium sweepback angles;
the two missile wings are respectively arranged on two sides of the middle rear section of the missile body;
the two ailerons are respectively arranged at two sides of the rear section of the missile body and positioned at the rear edge end of the missile wing;
the vertical tail is a swallow-shaped vertical tail and is respectively arranged at two ends of the wing tip of the missile wing;
the interstage transition cabin is connected with the mission stage and the booster in series, and is a cone with an expansion angle of 22.5 degrees;
the booster body is positioned at the rear end of the interstage transition cabin and adopts a straight section with a circular cross section; and the rotating tail wings are arranged at the tail part of the booster body.
Further, the sweep angle of the front edge of the duck wing is 45 degrees, the wingspan is 720mm, the root ratio is 0.7, the duck wing airfoil is an optimized airfoil based on 6% NACA standard airfoil, and the front edge of the airfoil is mainly optimized to delay the occurrence of local supersonic speed.
Further, the sweepback angle of the front edge of the missile wing is 72 degrees, the wingspan is 1200mm, the length of the root of the missile wing is 1900mm, and the length of the tip of the missile wing is 555 mm. The airfoil is an optimized and improved airfoil based on a NACA6400 airfoil reduced head radius.
Furthermore, the ailerons smoothly transition with the missile wing trailing edge under the extreme deflection angle to weaken the shock wave of the aileron leading edge during supersonic flight and improve the control surface efficiency.
Further, the vertical tail adopts a supersonic speed common hexagonal wing section.
Furthermore, the rotating tail wing is a swept-back trapezoidal wing, and the wing type adopts a supersonic speed common hexagonal wing type.
The invention has the advantages and beneficial effects that: the aerodynamic shape provided by the invention can enable the target to fly in a wide speed range, and meanwhile, the target with the aerodynamic shape has excellent aerodynamic performance and good manipulation performance during supersonic speed large maneuvering flight, fills the blank in the field of supersonic speed large maneuvering targets, and can meet the requirements of novel weapon identification and war training.
Drawings
FIG. 1 is a flight overload curve.
FIG. 2 is a plot of flight Mach number.
FIG. 3 is a top view of the aerodynamic profile of the target.
FIG. 4 is a side view of the aerodynamic profile of the target.
FIG. 5 is a front view of the aerodynamic profile of the target.
The numbers in the figures illustrate the following:
the missile comprises a head cover 1, canard wings 2, a middle and rear missile body section 3, missile wings 4, an interstage transfer cabin 5, a booster missile body 6, a rotary tail wing 7, ailerons 8 and a vertical tail 9.
Detailed Description
By applying the technical scheme, the hood of the invention adopts a von Karman molded line, so that the flight resistance can be reduced, and the middle and rear sections of the bullet body adopt equivalent sections with circular sections to meet the loading requirements of equipment and the like; the two canard wings are respectively arranged at two sides of the hood, the trapezoidal wings with medium sweepback angles are adopted, the sweepback angle is 45 degrees, the span length is 720mm, the planar shape of the trapezoidal wings effectively inhibits airflow separation on the surfaces of the canard wings at a supersonic speed and a large attack angle, and sufficient control surface efficiency is ensured during large maneuvering flight. The two missile wings are respectively arranged at two sides of the middle rear section of the missile body, the missile wings adopt large sweepback sharp-cutting delta wings, the sweepback angle is 72 degrees, the wingspan is 1200mm, and the missile wings mainly provide the lifting force for the supersonic cruise flight and the maneuvering flight of the target; the two vertical tails are respectively arranged at two sides of the wing tip of the missile wing, the sweepback angle of the front edge of the vertical tail is 37 degrees, the vertical height is 560mm, the length of the root chord of the vertical tail is 557mm, the slight chord length is 314mm, and the vertical tail mainly provides enough course stability for a target. The two ailerons have the face width of 120mm, the spanwise length of 435mm and the base of the aileron axle is 100mm from the tail edge, and the ailerons can be matched with canards to control the pitch direction of the target during supersonic high-mobility flight or control the roll direction of the target through differential deflection of the ailerons. The interstage transition cabin adopts a conical body with a half cone angle of 22.5 degrees. The tail part of the booster is provided with the rotary tail wing, the wing span of the rotary tail wing is 2250mm, the sweepback angle of the front edge is 70 degrees, the slightly root ratio is 0.45, and the rotary tail wing can ensure that the target has enough pitching and yawing static stability in a boosting flight section so as to meet the requirements of a control system.
In addition to the above described features and objects, there are other objects, features and advantages of the present invention. The invention is described in further detail below with reference to fig. 1-5.
As shown in a target flight overload curve of fig. 1, the stable overload of the target in the maneuvering flight section lasts about 6g, and large maneuvering flight is realized;
as shown in a target flight mach number curve of fig. 2, the mach number of the target in the maneuvering flight section can reach 1.6, and the target realizes supersonic large maneuvering flight;
as shown in the top view of the target aerodynamic profile in FIG. 3 and the side view of the target aerodynamic profile in FIG. 4, the invention provides a supersonic large aerodynamic target aerodynamic profile, which comprises a head cover 1, canards 2, a middle and rear missile body section 3, missile wings 4, an interstage transition cabin 5, a booster missile body 6, a rotating tail 7, ailerons 8 and a vertical tail 9. Wherein two duck wings 2 link firmly in hood 1 both sides, and two missile wings 4 link firmly in 3 both sides of body of a bullet, and two ailerons 8 pass through hinged joint at the 4 trailing edges of both sides missile wing, and back section 3 and booster body of a bullet 6 in the body of a bullet are connected to interstage surge tank 5.
As shown in the top view of the pneumatic appearance of the target in fig. 3 and the front view of the pneumatic appearance of the target in fig. 5, four rotating tail wings 7 are uniformly distributed at the rear end of the booster projectile body 6 and are fixedly connected to the booster projectile body 6.
As shown in fig. 3, the hood 1 adopts a Von Karman curve as a hood profile, the slenderness ratio of the hood is 3.3, and the slenderness ratio and the head profile can effectively reduce the resistance of a target in flight.
As shown in figure 3, the middle and rear sections of the bullet body are circular and have the same cross section, and the diameter of the bullet body is 330mm
As shown in figure 3, two duck wings 2 are respectively arranged at two sides of the head cover 1, and adopt trapezoidal wings with medium sweepback angles, the sweepback angle is 45 degrees, the spread length is 720mm, and the root ratio is 0.3. When the target is in supersonic speed large maneuvering flight, the canard wing is the main pitching control surface, and the guarantee of sufficient rudder effect is the key factor for realizing the large maneuvering flight of the target. When the aircraft flies by maneuvering, the attack angle of the aircraft is large, the deflection angle of the canard wing rudder is consistent with the direction of the attack angle, so the actual attack angle of the canard wing is very large, the actual attack angle of the canard wing can be as high as 25 degrees, and under the working condition of the large attack angle, airflow separation is easy to occur on the surface of the canard wing. The shock wave generated at the head of the duck wing can be effectively delayed by adopting a larger wing surface sweepback angle, so that the airflow separation generated on the surface of the duck wing during maneuvering flight is delayed, and the rudder effect of the duck wing is ensured. The large aspect ratio and wing area can ensure that the canard provides enough lift force, thereby ensuring the maneuvering demand of the control surface during maneuvering.
As shown in figure 3, two missile wings 4 are respectively arranged at two sides of the middle rear section 3 of the missile body, the missile wings adopt large-sweepback sharp-cutting delta wings, the sweepback angle is 72 degrees, the wingspan is 1200mm, the length of the wing root of the missile wing is 1900mm, the length of the wing tip is 557mm, and the missile wings mainly provide the lifting force for the target supersonic cruise flight and maneuver flight. Because the target adopts a ground boosting launching mode, a boosting flight section and a climbing section, the flying speed of the target is very high and can reach 2.5Ma at most, and in order to reduce the flight resistance and reduce the energy loss of the target in the boosting flight and climbing processes, the missile wing adopts the appearance of a missile wing with a large sweepback angle and a small aspect ratio; large maneuvering operations require the target to provide sufficient lift, so that the large root and tip lengths of the wing provide the target with sufficient wing area to provide lift during maneuvering operations.
As shown in fig. 4 and 5, two vertical tails 9 are respectively arranged at two ends of the wing tip of the missile wing 4, the sweepback angle of the front edge of the vertical tail is 37 degrees, the vertical height is 560mm, the string length of the root of the vertical tail is 557mm, and the slight string length is 314 mm; the target does not carry out lateral control in the flight process, and the effect of end-to-end mainly provides sufficient driftage static stability for the target in whole flight process. When the aircraft flies at a supersonic speed with a large attack angle, the front edge of the vertical tail is easy to generate shock waves, the separation of the surface of the vertical tail is induced, the shape of the surface of the vertical tail can effectively delay the shock waves of the front edge of the vertical tail at the supersonic speed, and the separation phenomenon of the surface of the vertical tail is inhibited, so that the aerodynamic characteristics of the vertical tail are ensured to ensure enough course stability.
As shown in figure 3, the two flaps 8 are 120mm wide and 435mm long in the spanwise direction; the axial distance between the ailerons and the tail edge is 100mm, the two ailerons 8 are respectively arranged at the rear edge of the missile wing 4, the ailerons 8 and the canard wing 2 are combined to perform longitudinal pitching control of a target, and the ailerons are designed to ensure that the ailerons can be in smooth transition with the rear edge of the missile wing when the extreme rudder deviates, so that the shock wave phenomenon on the surfaces of the ailerons at supersonic speed is delayed, the sufficient control surface efficiency of the ailerons is ensured, and the resistance increase caused by the deviation of the aileron rudder is reduced. The maximum control plane deflection angle of the aileron can reach 15 degrees, sufficient control plane efficiency can be provided, and the control requirement of supersonic speed large maneuvering flight is met.
As shown in fig. 3, the interstage transition compartment 5 connects the middle and rear sections 3 of the body of the bomb and the body 6 of the booster, the length of the interstage transition compartment is 255mm, and the diameter of the front end of the interstage compartment is as follows:
rear end diameter of interstage compartment:
the size of the conical divergence angle of the transition cabin not only influences the resistance of the target boosting flight section, but also causes too large conical divergence angle, too large resistance of supersonic flight of the boosting flight section and too large energy loss. The conical expansion angle is too small, so that the safe and reliable separation of the booster is influenced, and the half cone angle is set to be 22.5 degrees, so that the target can be ensured to have small enough resistance in the boosting flight section while the safe and reliable separation of the booster is ensured.
As shown in FIG. 3, the booster body 6 has a circular cross section of the same size and a diameter of 400 mm.
As shown in figures 3 and 4, four pieces of rotating tail wings 7 are uniformly distributed on the tail end face of the booster missile body 6, the wingspan of the rotating tail wings is 2250mm, the sweepback angle of the front edge is 70 degrees, and the sweepback angle is slightly larger than 0.45. The fin can satisfy the stability demand of boosting flight segment target. The target does not control pitching and yawing directions in the boosting flight section, so that the cost of two steering engines can be reduced, enough longitudinal and course static stability must be guaranteed, the longitudinal and course stability of the target is mainly realized by the aid of the rotating tail wing, and the rotating tail wing at the tail of the booster can provide enough aerodynamic force to pull a focus to move backwards so as to meet the requirement on the stability of the target boosting flight section due to the fact that the rotating tail wing provided by the target missile wing has a large lifting surface. In order to prevent the wash flow of the ailerons from inducing opposite roll torque on the rotating tail wing when the ailerons are differentially deflected to carry out the roll control, and the roll control efficiency of the ailerons is lost, the rotating tail wing is adopted to freely rotate so as to eliminate the influence of the wash flow of the ailerons.
Claims (10)
1. A supersonic speed large maneuvering target pneumatic shape; it is characterized by comprising: the missile comprises a head cover, duck wings, a middle and rear section of a missile body, missile wings, an interstage transition cabin, a booster missile body, a rotary tail wing, ailerons and a vertical tail; wherein the hood is molded by von Karman curve lofting; the two duck wings are respectively arranged at two ends of the head cover, and the duck wings adopt trapezoidal wings with medium sweepback angles; the middle-rear section of the bullet body is positioned at the rear end of the head cover and adopts a straight section with a circular cross section; the two missile wings are respectively arranged on two sides of the middle rear section of the missile body; the interstage transition cabin is connected with the task stage and the booster in series; the booster body is positioned at the rear end of the interstage transition cabin and adopts a straight section with a circular cross section; the number of the rotary tail wings is four, and the rotary tail wings are arranged at the tail part of the booster body; the two ailerons are respectively arranged at two sides of the back section of the missile body and are positioned at the back edge end of the missile wing; the vertical tail is a swallow-shaped vertical tail and is respectively arranged at two ends of the wing tip of the missile wing.
2. A supersonic large maneuvering target aerodynamic profile according to claim 1; the method is characterized in that: the sweepback angle of the duck wing leading edge is 45 degrees, the wingspan is 720mm, the root ratio is 0.7, the duck wing airfoil is an optimized airfoil based on 6% of NACA standard airfoil, and the airfoil leading edge is optimized to delay the occurrence of local supersonic speed.
3. A supersonic large maneuvering target aerodynamic profile according to claim 1; the method is characterized in that: the sweepback angle of the front edge of the missile wing is 72 degrees, the wingspan is 1200mm, the length of the root of the missile wing is 1900mm, and the length of the tip of the missile wing is 555 mm; the airfoil is an optimized and improved airfoil based on a NACA6400 airfoil reduced head radius.
4. A supersonic large maneuvering target aerodynamic profile according to claim 1; the method is characterized in that: the ailerons and the missile wing trailing edge are in smooth transition under the extreme deflection angle so as to weaken shock waves of the aileron leading edge during supersonic flight and improve the control surface efficiency.
5. A supersonic large maneuvering target aerodynamic profile according to claim 1; the method is characterized in that: the vertical tail adopts supersonic speed hexagonal wing type.
6. A supersonic large maneuvering target aerodynamic profile according to claim 1; the method is characterized in that: the rotary tail wing is a swept-back trapezoidal wing and adopts a supersonic hexagonal wing type.
7. A supersonic large maneuvering target aerodynamic profile according to claim 1 or 4; the method is characterized in that: the maximum rudder surface deflection angle of the aileron can reach 15 degrees.
8. A supersonic large maneuvering target aerodynamic profile according to claim 1; the method is characterized in that: the interstage transition cabin is a cone with a divergence angle of 22.5 degrees.
9. A supersonic large maneuvering target aerodynamic profile according to claim 1 or 2; the method is characterized in that: when the aircraft flies in a maneuvering manner, the attack angle of the aircraft is large, the deflection angle of the canard wing rudder is consistent with the attack angle direction, the actual attack angle of the canard wing can reach 25 degrees, and the maneuvering capability of the target is effectively improved.
10. A supersonic large maneuvering target aerodynamic profile according to claim 1, or 2, or 3, or 4, or 5, or 6, or 7, or 8, or 9; the method is characterized in that: the target adopts a ground boosting launching mode, and the mission stage and the booster are connected in series through the interstage transition cabin; the target aerodynamic shape can realize 8-14 km large airspace, 0.8-1.6 Ma wide speed range and stable 6g flight, and supersonic speed large-maneuvering flight under a large-maneuvering wide flight envelope of instantaneous 9g flight.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111317850.0A CN114104254A (en) | 2021-11-09 | 2021-11-09 | Pneumatic appearance structure of supersonic speed large maneuvering target |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111317850.0A CN114104254A (en) | 2021-11-09 | 2021-11-09 | Pneumatic appearance structure of supersonic speed large maneuvering target |
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| CN114104254A true CN114104254A (en) | 2022-03-01 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115507707A (en) * | 2022-09-30 | 2022-12-23 | 西安航天动力研究所 | Pneumatic layout of supersonic speed large mobile stealth target |
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| WO2015065551A1 (en) * | 2013-07-25 | 2015-05-07 | Lam Aviation, Inc. | Aircraft wing structure and control system |
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| CN107990792A (en) * | 2017-12-28 | 2018-05-04 | 北京威标至远科技发展有限公司 | A kind of rotatable tail gear |
| CN109229404A (en) * | 2018-10-23 | 2019-01-18 | 西北工业大学 | A kind of unmanned plane slide rail type quick recovery system in the air |
| CN213192507U (en) * | 2020-10-15 | 2021-05-14 | 罗翌铭 | Manual remote control flying wing for teaching |
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2021
- 2021-11-09 CN CN202111317850.0A patent/CN114104254A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102155885A (en) * | 2010-12-31 | 2011-08-17 | 北京威标至远科技发展有限公司 | Cruise target projectile |
| WO2015065551A1 (en) * | 2013-07-25 | 2015-05-07 | Lam Aviation, Inc. | Aircraft wing structure and control system |
| CN106428560A (en) * | 2016-10-28 | 2017-02-22 | 中国人民解放军总参谋部第六十研究所 | Canard aerodynamic configuration of subsonic-velocity high-maneuver drone aircraft |
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| CN115507707A (en) * | 2022-09-30 | 2022-12-23 | 西安航天动力研究所 | Pneumatic layout of supersonic speed large mobile stealth target |
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