CN110065649A - Using the near space hypersonic aircraft ballistic design method of virtual aim point - Google Patents
Using the near space hypersonic aircraft ballistic design method of virtual aim point Download PDFInfo
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- CN110065649A CN110065649A CN201910389092.XA CN201910389092A CN110065649A CN 110065649 A CN110065649 A CN 110065649A CN 201910389092 A CN201910389092 A CN 201910389092A CN 110065649 A CN110065649 A CN 110065649A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
Abstract
Using the near space hypersonic aircraft ballistic design method of virtual aim point, belongs to ballistic design field, be related to a kind of ballistic design method.The present invention is in order to solve the problems, such as that the ballistic design method of existing proportional guidance is difficult to reach target point and be not able to satisfy the angle of fall to require there are aircraft.The aircraft flight stage is divided into cruise section and pushes section by the present invention, chooses a virtual target point at interval of K1 distance in cruise section, and choosing lower pressure point is xk；Then it is designed according to the principle that virtual aim point is chosen, cruise section requires height change between any two adjacent virtual aiming point to be no more than 5km, and the trajectory of design is approximately the form of SIN function in fore-and-aft plane；Away from final goal point distance K3, the last one virtual aim point coordinate is determined by optimizing algorithm.The present invention is used near space hypersonic aircraft ballistic design.
Description
Technical field
The invention belongs to ballistic design fields, are related to a kind of ballistic design method.
Background technique
The usual flying distance of near space hypersonic aircraft is in 5000km or more, it might even be possible to reach 10000km.Face
Near space hypersonic aircraft is usually maintained at high-speed flight near space 40km height after atmospheric reentry, away from mesh
Height target of attack is reduced rapidly when punctuate 150km or so.When the aircraft to this long range carries out ballistic design, if from
Atmospheric reentry moment direct use ratio guidance method at target point designs trajectory, aircraft can be made to enter atmosphere too early
The biggish low-latitude flying of density keeps aircraft speed loss very big, it is difficult to reach target point.Meanwhile hypersonic aircraft exists
Difficulty is intercepted in order to increase defender when target of attack, usually there is the requirement of the angle of fall, is difficult to using single proportional navigation method full
The foot angle of fall requires.
Summary of the invention
The present invention is to solve the ballistic design method of existing proportional guidance to be difficult to reach target point there are aircraft and cannot
Meet the problem of angle of fall requires.
Using the near space hypersonic aircraft ballistic design method of virtual aim point, comprising the following steps:
Choose virtual aim point:
The aircraft flight stage is divided into two sections, cruise section and pushes section；
A virtual target point is chosen at interval of K1 distance in cruise section, is denoted as x1、x2…xk-1；Choosing lower pressure point is
xk, then it is Ox by the flight path the initial point O of atmospheric reentry stabilized flight1→x1x2…→xk-1xk；At aircraft
In Ox1When, x1As virtual aim point, x is flown to using proportional navigation method1Point, when aircraft reaches x1After point, by x2As virtual
Aiming point flies to x using proportional navigation method2Point, and so on；
The principle that virtual aim point is chosen:
In order to keep aircraft in the ability of cruise section high-speed flight, it is desirable that the angle of attack and yaw angle of cruise section aircraft begin
It is maintained within 5 ° eventually.Big ups and downs do not occur in order to guarantee that the angle of attack remains within 5 °, cruise section requires any two
Height change is no more than 5km between adjacent virtual aiming point, and the trajectory of design is approximately the shape of SIN function in fore-and-aft plane
Formula；Meanwhile to guarantee that yaw angle is relatively small, under initial inertial coodinate system, two adjacent virtual aiming point it is lateral away from
From should be relatively small, under the selection principle of K1, lateral distance should be less than 50km on schedule in any two virtual face；
For the last one virtual aim point xkIf aircraft, which flies to final goal point, wanting for the angle of fall and end speed
It asks, by xkSetting coordinate be variable, the point that meets the requirements is chosen as x by optimizing algorithmk, the point away from final goal point away from
From K3.
Further, the pushing section is 100km to 200km.Preferably, the pushing section is 150km.
Further, K1 is 485km to 510km.Preferably, K1 500km.
Further, K3 is 100km to 200km.Preferably, K3 150km.
Present invention feature the most prominent and significant beneficial effect are:
It can be designed that the trajectory of near space hypersonic aircraft using the present invention, and can be protected by emulation experiment
It demonstrate,proves aircraft and reaches target, and can guarantee the angle of fall and end speed etc. and require.
It is highly target point at 50km, initially for Mr. Yu's hypersonic aircraft from distance objective point 4200km
Speed is 20 Mach or so.By choosing 8 suitable virtual aim points, a normal trajectory, end speed can be had devised
For Vt=803.67m/s.
Detailed description of the invention
Fig. 1 is the relational graph of position of aircraft coordinate x under aircraft altitude and inertial coodinate system；
Fig. 2 is aircraft away from target point distance and time chart；
Fig. 3 is aircraft and speed and time chart；
Fig. 4 is Aircraft Angle of Attack and time chart；
Fig. 5 is aircraft yaw angle and time chart；
Fig. 6 is position of aircraft coordinate z-x relational graph under inertial system.
Specific embodiment
Specific embodiment 1:
Using the near space hypersonic aircraft ballistic design method of virtual aim point, comprising the following steps:
One, virtual aim point is chosen:
The aircraft flight stage is divided into two sections, cruise section and pushes section, wherein pushing section about 150km or so.It is cruising
Section chooses a virtual target point at interval of K1 about 500km or so, is denoted as x1、x2…xk-1, choosing lower pressure point is xk, then by again
Entering the flight path that the initial point O of atmosphere stabilized flight starts is Ox1→x1x2…→xk-1xk.When aircraft is in Ox1When,
x1As virtual aim point, x is flown to using proportional navigation method1Point, when aircraft reaches x1After point, by x2As virtual aim point,
X is flown to using proportional navigation method2Point, and so on.
It is directed to for K1, is able to satisfy requirement substantially in 485km to 510km.
Two, the principle that virtual aim point is chosen:
Near space vehicle is maintained at 40km or so in cruise section flying height, and aircraft can be made when flying height is lower
The angle of attack and yaw angle excessive by resistance while excessive equally will increase the resistance that aircraft is subject to, and excessive resistance can make
Aircraft is difficult to arrive at target point.Therefore, it is the speed for keeping aircraft, should be kept in cruise section Aircraft Angle of Attack and yaw angle
The relatively small value within 5 °, this requires height change is relatively small between two adjacent virtual aim points, any two
Height change is no more than 5km between a adjacent virtual aiming point.
If aircraft is according to equal angles of attack state follow-on mission, the trajectory of flight can be approximately SIN function in fore-and-aft plane
Form, in order to guarantee that big ups and downs do not occur for a small range that the angle of attack remains within 5 °, when choosing virtual aim point,
The trajectory that can make design is approximately sinuous state in fore-and-aft plane.Meanwhile to guarantee that yaw angle is relatively small, it is used in initial
Under property coordinate system, the lateral distance of two adjacent virtual aiming point should be relatively small, distance herein it is relatively small with it is entire
The number of length and the virtual aim point of trajectory, aircraft are initially at size of lateral initial velocity components etc. because being known as
It closes, if being 4200km by Trajectory Length in simulation example, virtual aim point takes 8, the initial velocity point of initial lateral
Amount is 0, then lateral distance is less than 50km between any two adjacent virtual aiming point.Ballistic range is shorter, virtual aim
Point number is more, then adjacent distance between two points are smaller.Ignore the influence of initial velocity factor, the first two factor can be equivalent to K1
Selection principle, under the selection principle of K1, lateral distance should be less than 50km on schedule in any two virtual face.Ballistic design is divided into
The design rule of lateral plane and fore-and-aft plane, lateral plane and fore-and-aft plane needs to meet simultaneously.
For the last one virtual aim point xkIf aircraft, which flies to final goal point, wanting for the angle of fall and end speed
It asks, it can be by xkSetting coordinate be variable, the point that meets the requirements is chosen as x by optimizing algorithmk.The point is away from final goal point
Distance K3 is generally 150km or so.Here by optimizing algorithm it is confirmed that xkCoordinate, be at a distance from final goal point
K3, K3 are in 100km to 200km range, generally 150km or so.
Embodiment
Emulation experiment is carried out using the present invention.Certain hypersonic aircraft is highly 50km from distance objective point 4200km
Locate target point, initial velocity is 20 Mach or so.By choosing 8 suitable virtual aim points, an orderliness is had devised
Think trajectory, end speed Vt=803.67m/s.Specific simulated effect is as shown in Fig. 1 to Fig. 6, wherein Fig. 1 flies for aircraft
The relational graph of row height and position of aircraft coordinate x under inertial coodinate system；Fig. 2 is aircraft away from target point distance and time relationship
Figure；Fig. 3 is aircraft and speed and time chart；Fig. 4 is Aircraft Angle of Attack and time chart；Fig. 5 is aircraft sideslip
Angle and time chart；Fig. 6 is position of aircraft coordinate z-x relational graph under inertial system.
Claims (7)
1. using the near space hypersonic aircraft ballistic design method of virtual aim point, which is characterized in that including following
Step:
Choose virtual aim point:
The aircraft flight stage is divided into two sections, cruise section and pushes section；
A virtual target point is chosen at interval of K1 distance in cruise section, is denoted as x1、x2…xk-1；Choosing lower pressure point is xk, then
It is Ox by the flight path the initial point O of atmospheric reentry stabilized flight1→x1x2…→xk-1xk；When aircraft is in Ox1
When, x1As virtual aim point, x is flown to using proportional navigation method1Point, when aircraft reaches x1After point, by x2As virtual aim
Point flies to x using proportional navigation method2Point, and so on；
The principle that virtual aim point is chosen:
In order to keep aircraft in the ability of cruise section high-speed flight, it is desirable that the angle of attack and yaw angle of cruise section aircraft are protected always
It holds within 5 °；Big ups and downs do not occur in order to guarantee that the angle of attack remains within 5 °, cruise section requires any two adjacent
Height change is no more than 5km between virtual aim point, and the trajectory of design is approximately the form of SIN function in fore-and-aft plane；Together
When, to guarantee that yaw angle is relatively small, under initial inertial coodinate system, two lateral distances of adjacent virtual aiming point should
Relatively small, under the selection principle of K1, lateral distance should be less than 50km on schedule in any two virtual face；
For the last one virtual aim point xkIf aircraft flies to the requirement that final goal point has the angle of fall and end speed, by xk
Setting coordinate be variable, the point that meets the requirements is chosen as x by optimizing algorithmk, the point is away from final goal point distance K3.
2. the near space hypersonic aircraft ballistic design method of virtual aim point is used according to claim 1,
It is characterized in that, the pushing section is 100km to 200km.
3. the near space hypersonic aircraft ballistic design method of virtual aim point is used according to claim 2,
It is characterized in that, the pushing section is 150km.
4. according to claim 1, the 2 or 3 near space hypersonic aircraft ballistic design side using virtual aim point
Method, which is characterized in that K1 is 485km to 510km.
5. the near space hypersonic aircraft ballistic design method of virtual aim point is used according to claim 4,
It is characterized in that, K1 500km.
6. according to claim 1, the 2 or 3 near space hypersonic aircraft ballistic design side using virtual aim point
Method, which is characterized in that K3 is 100km to 200km.
7. the near space hypersonic aircraft ballistic design method of virtual aim point is used according to claim 6,
It is characterized in that, K3 150km.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112445230A (en) * | 2019-08-27 | 2021-03-05 | 北京理工大学 | High-dynamic aircraft multi-mode guidance system and guidance method under large-span complex environment |
| CN115289908A (en) * | 2022-06-07 | 2022-11-04 | 西北工业大学 | Method and device for guiding air defense missile introduction section through remote control instruction |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120143505A1 (en) * | 2010-12-07 | 2012-06-07 | Airbus Operations (S.A.S.) | Method And Device For Determining An Optimal Flight Trajectory Followed By An Aircraft |
| CN104778376A (en) * | 2015-05-04 | 2015-07-15 | 哈尔滨工业大学 | Method for predicting skipping trajectory of hypersonic glide warhead in near space |
| CN104777844A (en) * | 2015-02-12 | 2015-07-15 | 西安电子科技大学 | Method for tracking trajectories of hypersonic velocity near space aircraft |
| CN107966156A (en) * | 2017-11-24 | 2018-04-27 | 北京宇航系统工程研究所 | A kind of Design of Guidance Law method suitable for the vertical exhausting section of carrier rocket |
| CN109031219A (en) * | 2018-06-14 | 2018-12-18 | 西安电子科技大学 | Wideband radar Ballistic Target fine motion geometric parameter estimation method based on phase ranging |
-
2019
- 2019-05-10 CN CN201910389092.XA patent/CN110065649B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120143505A1 (en) * | 2010-12-07 | 2012-06-07 | Airbus Operations (S.A.S.) | Method And Device For Determining An Optimal Flight Trajectory Followed By An Aircraft |
| CN104777844A (en) * | 2015-02-12 | 2015-07-15 | 西安电子科技大学 | Method for tracking trajectories of hypersonic velocity near space aircraft |
| CN104778376A (en) * | 2015-05-04 | 2015-07-15 | 哈尔滨工业大学 | Method for predicting skipping trajectory of hypersonic glide warhead in near space |
| CN107966156A (en) * | 2017-11-24 | 2018-04-27 | 北京宇航系统工程研究所 | A kind of Design of Guidance Law method suitable for the vertical exhausting section of carrier rocket |
| CN109031219A (en) * | 2018-06-14 | 2018-12-18 | 西安电子科技大学 | Wideband radar Ballistic Target fine motion geometric parameter estimation method based on phase ranging |
Non-Patent Citations (6)
| Title |
|---|
| 朱建文等: "高超声速飞行器俯冲机动最优制导方法", 《国防科技大学学报》 * |
| 王继平等: "一种虚拟目标点的弹道迭代确定方法", 《飞行力学》 * |
| 秦雷等: "临近空间非弹道式目标HTV-2跟踪滤波与预报问题", 《航天控制》 * |
| 罗超等: "一种带有过渡因子的下压指令设计方法", 《海军航空工程学院学报》 * |
| 胡诗国等: "一种近空间高超声速飞行器的制导律设计与仿真", 《弹道学报》 * |
| 黄佩等: "带落角约束的高超声速飞行器轨迹仿真研究", 《导弹与航天运载技术》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112445230A (en) * | 2019-08-27 | 2021-03-05 | 北京理工大学 | High-dynamic aircraft multi-mode guidance system and guidance method under large-span complex environment |
| CN112445230B (en) * | 2019-08-27 | 2021-12-24 | 北京理工大学 | High-dynamic aircraft multi-mode guidance system and guidance method under large-span complex environment |
| CN115289908A (en) * | 2022-06-07 | 2022-11-04 | 西北工业大学 | Method and device for guiding air defense missile introduction section through remote control instruction |
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