CN109141802B - Simulation method for plug-in control law in capture trajectory test - Google Patents
Simulation method for plug-in control law in capture trajectory test Download PDFInfo
- Publication number
- CN109141802B CN109141802B CN201810868862.4A CN201810868862A CN109141802B CN 109141802 B CN109141802 B CN 109141802B CN 201810868862 A CN201810868862 A CN 201810868862A CN 109141802 B CN109141802 B CN 109141802B
- Authority
- CN
- China
- Prior art keywords
- rudder
- angle
- coefficient
- track
- hanging object
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a simulation method for a plug-in control law in a capture trajectory test. The controllable trajectory simulation of the airborne foreign objects under the condition of sub-span supersonic flow is realized. The real aerodynamic influence is better simulated by calculating the three-degree-of-freedom rudder deflection, so that the aim of improving the track capture precision is fulfilled. The method adopts a virtual rudder deflection mode, and adds the influence quantity generated by rudder deflection into the track prediction according to the predicted rudder deflection of the external hanging object and the rudder effect obtained by the test. The method can simulate the influence of the control law of the stores on the track of the stores, acts on the track capture test and influences the pneumatic result and the generated track in real time. The generated influence is added into the track prediction through the calculation and analysis of the virtual rudder deviation and the experimental rudder effect, so that the precision of the track prediction is improved.
Description
Technical Field
The invention relates to the technical field of wind tunnel tests, in particular to a simulation method for an external store control law in a capture trajectory test.
Background
The wind tunnel foreign object capturing track test is a test technology for obtaining the motion track of a foreign object, the foreign object is installed on a multi-degree-of-freedom test system, information such as the pose track of the foreign object is obtained through motion and measurement in a wind tunnel flow field environment, and the wind tunnel foreign object capturing track test can simulate the flight track of the foreign object after being thrown from a carrier or being emitted and separated. Due to the limitation of the size of the wind tunnel, the size of the plug-in model is small, the control surface can not actually deflect and change, and the flight state of the plug-in model is different from that of a plug-in object, and the deflection change of the control surface has interaction with a flow field of a surrounding space and aerodynamic force change in the multi-body separation process, so that the accuracy of launching or throwing direction of the plug-in object is greatly influenced.
Disclosure of Invention
In order to research the influence of the deviation of the rudder of the store on the real-time flight trajectory in the wind tunnel store capture trajectory test, the invention provides a simulation method for the store control law in the capture trajectory test, which simulates the influence of the deviation of the rudder of the store on the real-time trajectory and improves the precision of the trajectory capture test.
The technology adopted by the invention is as follows: a simulation method for capturing pendant control laws in trajectory trials, the method comprising the steps of:
step 1, calculating the estimated position of a track point of the external store, calculating and obtaining the instantaneous acceleration, the angular velocity and the angle of the track point, and positioning the estimated track of the external store in real time;
step 2, actually measuring the stress of the external hanging objects in the specified flow field and the real-time hexabasic balance in the wind tunnel, and carrying out pneumatic resolving;
step 3, adopting a virtual rudder deflection mode, and resolving the rudder deflection of the external stores;
step 4, combining rudder deflection and aerodynamic force, and calculating the rudder effect of the external stores in real time;
and 5, correcting the rudder effect iteration track points of the variable-step-length external hanging object.
The invention also has the following technical characteristics:
1. the step 1 is as follows:
f is the trace point instantaneous acceleration: f coe × qs × refS
In the formula, coe is a aerodynamic coefficient, qs is an upper speed pressure at a specified height, and refS is a reference area;
alpha _ e is the angle of attack of the store, and the calculation formula is as follows:
in the formula, phiw、θw、ψwThree angular displacements of the plug-in object relative to an air shaft system of the aircraft are obtained;
kkthita _ e is the pitching angle of the external hanging object, namely the included angle between the X axis of the external hanging object and the horizontal plane:
kkthita_e＝θw
psi _ e is the external hanging course angle, namely the included angle between the projection of the X axis of the external hanging in the horizontal plane and the projection of the X axis of the airplane in the horizontal plane:
psi_e＝ψw+β
wherein β is the sideslip angle;
gama _ e is the cross roll angle of the external hanging object, namely the included angle between the longitudinal symmetrical plane of the external hanging object and the vertical plane passing through the X axis of the external hanging object:
gama_e＝φw
dkkthita_e、dpsi_e、dgama_echange rate of pitch angle, change rate of course angle and change rate of roll angle of the outer hanging object:
dkkthita_e＝qEcosφw-rEsinφw
dpsi_e＝(qEsinφw+rEcosφφw)/cosθw
dgama_e＝pE+dpsi_e·sinθw
in the formula, pE、qE、rEIs the projection of the angular velocity of the outer hanging object on three axes of the body axis of the outer hanging object.
2. The pneumatic calculation is performed as in step 2 above, specifically as follows:
cynormal force coefficient:
cztransverse force coefficient:
Cmzpitching moment coefficient:
Cmyyaw moment coefficient:
Cmxroll moment coefficient:
in the formula, Y is a lift force, Z is a transverse force, Mz is a pitching moment, My is a yawing moment, Mx is a rolling moment, b is an average aerodynamic chord length, and l is a wing extension length.
3. The method for resolving the rudder deflection of the external hanging object in the step 3 specifically comprises the following steps:
delta1 rudder deflection angle 1:
Delta1＝b1×D1[1][1]+b2×D1[1][0]+b3×D1[0][2]+b4×D1[0][1]；
delta2 rudder deflection angle 2:
Delta2＝b1×D2[1][1]+b2×D2[1][0]+b3×D2[0][2]+b4×D2[0][1]；
delta3 rudder angle 3:
Delta3＝b1×D3[1][1]+b2×D3[1][0]+b3×D3[0][2]+b4×D3[0][1]；
in the formula, b1, b2, b3 and b4 are command control gain parameters, D1, D2 and D3 are interpolation arrays of the aerodynamic rudder deflection angle and the airflow attack angle, and numbers in brackets in the formula represent array dimensions.
4. The method for real-time calculation of the rudder effect of the store by combining rudder deflection and aerodynamic force in the step 4 is specifically as follows:
Δ cy: y-direction steering force coefficient rudder effect increment: Δ cy ═ (c1-c2) × Kcy;
Δ cz: z-direction steering force coefficient rudder effect increment: Δ cz ═ (c1+ c2) × Kcz;
Δ cmx: roll moment coefficient rudder effect increment: Δ cmx ═ Kcmx 3;
Δ cmy: yaw moment coefficient rudder effect increment: Δ cmy ═ dcy × (tm-bp);
Δ cmz: pitching moment coefficient rudder effect increment: Δ cmz ═ dcz × (tm-bp);
in the formula, tm is a relative position of a mass center, bp is a relative position of a rudder axis, Kcy, Kcz and Kcmx are rudder efficiency coefficients, and c1, c2 and c3 are interpolation rudder deflection angles.
5. Step 5, the variable step length foreign object rudder effect iterative track point correction method specifically comprises the following steps:
cy: and the Y-direction operating force coefficient correction value: cy + Δ Cy
Cz is as follows: z-direction operating force coefficient correction value: cz + Δ Cz
Cmz: the pitching moment coefficient correction value is as follows: cmz＝Cmz+Δcmz
Cmx: roll torque coefficient correction value: cmx＝Cmx+Δcmx
Cmy: roll torque coefficient correction value: cmy＝Cmy+Δcmy。
The working process and principle of the invention are as follows: calculating the simulation pose, the instantaneous acceleration and the angle of the external hanging object according to initial conditions, accurately positioning the external hanging object, measuring the stress condition of the external hanging object through a balance, calculating the rudder deflection of the external hanging object according to experimental conditions, comprehensively analyzing and calculating the simultaneous data to obtain the rudder effect of the external hanging object, correcting the pose of the track, repeating the processes, simulating the real-time influence of the external hanging object on the track, and obtaining the controlled track of the external hanging object.
The invention has the advantages and beneficial effects that: the method can simulate the influence of the control law of the stores on the track of the stores, acts on the track capture test and influences the pneumatic result and the generated track in real time. The generated influence is added into the track prediction through the calculation and analysis of the virtual rudder deviation and the experimental rudder effect, so that the precision of the track prediction is improved. Through simulation comparison verification and example calculation verification, the method solves the problem of influence of simulation control surface deflection on the separation track of the hung object in the CTS test. The method has stable performance and high reliability, the test precision meets the engineering requirements, and the method has wide application prospect in the research of aviation and aerospace plug-in design and weaponry.
Drawings
FIG. 1 is a schematic block diagram of the structure of a plug-in control law simulation method in a trajectory capturing test according to the present invention;
FIG. 2 is a process control flow diagram of a plug-in control law simulation method for a trajectory capture test according to the present invention;
fig. 3 is a flow chart of rudder deflection effect simulation and calculation in the method for simulating the control law of the store in the trajectory capturing test provided by the invention.
Detailed Description
The invention is described in further detail below with reference to the accompanying drawings:
example 1
A simulation method for capturing a plug-in control law in a trajectory test comprises the following steps:
step 1, calculating the estimated position of the track point of the external store, calculating and acquiring the instantaneous acceleration, the angular velocity and the angle of the track point, and positioning the estimated track of the external store in real time, wherein the method specifically comprises the following steps: f is the trace point instantaneous acceleration: f coe × qs × refS
In the formula, coe is a aerodynamic coefficient, qs is an upper speed pressure at a specified height, and refS is a reference area;
alpha _ e is the angle of attack of the store, and the calculation formula is as follows:
in the formula, phiw、θw、ψwThree angular displacements of the plug-in object relative to an air shaft system of the aircraft are obtained;
kkthita _ e is the pitching angle of the external hanging object, namely the included angle between the X axis of the external hanging object and the horizontal plane:
kkthita_e＝θw
psi _ e is the external hanging course angle, namely the included angle between the projection of the X axis of the external hanging in the horizontal plane and the projection of the X axis of the airplane in the horizontal plane:
psi_e＝ψw+β
wherein β is the sideslip angle;
gama _ e is the cross roll angle of the external hanging object, namely the included angle between the longitudinal symmetrical plane of the external hanging object and the vertical plane passing through the X axis of the external hanging object:
gama_e＝φw
dkkthita_e、dpsi_e、dgama_echange rate of pitch angle, change rate of course angle and change rate of roll angle of the outer hanging object:
dkkthita_e＝qEcosφw-rEsinφw
dpsi_e＝(qEsinφw+rEcosφφw)/cosθw
dgama_e＝pE+dpsi_e·sinθw
in the formula, pE、qE、rEIs the projection of the angular velocity of the outer hanging object on three axes of the body axis of the outer hanging object.
Step 2, actually measuring the stress of the external hanging objects in the specified flow field and the real-time hexabasic balance in the wind tunnel, and carrying out pneumatic resolving; the method comprises the following specific steps:
cynormal force coefficient:
cztransverse force coefficient:
Cmzpitching moment coefficient:
Cmyyaw moment coefficient:
Cmxroll moment coefficient:
in the formula, Y is a lift force, Z is a transverse force, Mz is a pitching moment, My is a yawing moment, Mx is a rolling moment, b is an average aerodynamic chord length, and l is a wing extension length.
Step 3, adopting a virtual rudder deflection mode, and resolving the rudder deflection of the external stores; the method comprises the following specific steps:
delta1 rudder deflection angle 1:
Delta1＝b1×D1[1][1]+b2×D1[1][0]+b3×D1[0][2]+b4×D1[0][1]；
delta2 rudder deflection angle 2:
Delta2＝b1×D2[1][1]+b2×D2[1][0]+b3×D2[0][2]+b4×D2[0][1]；
delta3 rudder angle 3:
Delta3＝b1×D3[1][1]+b2×D3[1][0]+b3×D3[0][2]+b4×D3[0][1]；
in the formula, b1, b2, b3 and b4 are command control gain parameters, D1, D2 and D3 are interpolation arrays of the pneumatic rudder deflection angle and the airflow attack angle, and the number in brackets in the formula represents the array dimension;
step 4, combining rudder deflection and aerodynamic force, and carrying out real-time calculation on the rudder effect of the external stores, wherein the method specifically comprises the following steps:
Δ cy: y-direction steering force coefficient rudder effect increment: Δ cy ═ (c1-c2) × Kcy;
Δ cz: z-direction steering force coefficient rudder effect increment: Δ cz ═ (c1+ c2) × Kcz;
Δ cmx: roll moment coefficient rudder effect increment: Δ cmx ═ Kcmx 3;
Δ cmy: yaw moment coefficient rudder effect increment: Δ cmy ═ dcy × (tm-bp);
Δ cmz: pitching moment coefficient rudder effect increment: Δ cmz ═ dcz × (tm-bp);
in the formula, tm is a relative position of a mass center, bp is a relative position of a rudder axis, Kcy, Kcz and Kcmx are rudder efficiency coefficients, and c1, c2 and c3 are interpolation rudder deflection angles;
step 5, correcting the rudder effect iterative track points of the variable-step-length external hanging object, which specifically comprises the following steps:
cy: and the Y-direction operating force coefficient correction value: cy + Δ Cy;
cz is as follows: z-direction operating force coefficient correction value: cz + Δ Cz;
Cmz: the pitching moment coefficient correction value is as follows: cmz＝Cmz+Δcmz；
Cmx: roll torque coefficient correction value: cmx＝Cmx+Δcmx；
Cmy: roll torque coefficient correction value: cmy＝Cmy+Δcmy。
Example 2
As shown in fig. 1 and 2, firstly, the control law test conditions are loaded and judged, so that the loaded outer hanging object of the multi-degree-of-freedom mechanism is accurately positioned according to the preset conditions, the loaded outer hanging object is communicated with a wind tunnel, the wind tunnel control reaches the test flow field conditions, the outer hanging object rudder deflection calculation is fused through real-time aerodynamic force acquisition calculation and outer hanging object acceleration and attitude estimation, the real-time track is corrected point by point, and finally, the outer hanging object controlled track pose and the real-time rudder deflection effect in the test process are obtained.
While resolving the position of the track point, resolving to obtain the acceleration and angular velocity in each direction
The rolling angle Gama of the outer hanging object is-pi/4 + phi;
pitching acceleration of external hanging object
Yaw acceleration of an external hanging object
Pitch and yaw path angular velocities
Pitch and yaw path angular velocities
Roll angular velocity ω x is Pe;
as shown in fig. 3, in order to control the stability of the external stores, the above instantaneous air momentum is resolved by the stability control, and rudder deflection angle outputs of pitching, yawing and rolling channels are obtained. The aerodynamic force acting on the current outer hanging object is measured by an outer hanging balance to obtain a strain value, each aerodynamic force is obtained through seven iterations, and the influence of each rudder deflection angle on the aerodynamic force is calculated by combining each aerodynamic force of the current outer hanging object. Because the coordinate of the external store and the predicted coordinate system have deflection in a rolling direction with a certain angle, the coordinate deflection conversion is carried out on the related quantity, and 45-degree deflection is taken as an example.
Incremental Y-direction deflection operating force coefficient
Incremental Z-direction deflection operating force coefficient
Yaw roll moment coefficient increments dmx' ═ dmx;
yaw pitch moment coefficient delta
Yaw moment coefficient increment
In the formula, dcy is Y-direction manipulation force coefficient increment, dcz is Z-direction manipulation force coefficient increment, dmx is roll moment coefficient increment, dmz is pitch moment coefficient increment, and dmy is yaw moment coefficient increment;
and the rudder deflection influence of each track point is used for carrying out step length-variable iterative correction along with the change of the test time. Until all the vacant track points are finished.
Claims (3)
1. A simulation method for capturing a plug-in control law in a trajectory test is characterized by comprising the following steps:
step 1, calculating the estimated position of a track point of the external store, calculating and obtaining the instantaneous acceleration, the angular velocity and the angle of the track point, and positioning the estimated track of the external store in real time;
step 2, actually measuring the stress of the external hanging objects in the specified flow field and the real-time hexabasic balance in the wind tunnel, and carrying out pneumatic resolving;
step 3, adopting a virtual rudder deflection mode, and resolving the rudder deflection of the external stores, wherein the method specifically comprises the following steps:
delta1 rudder deflection angle 1:
Delta1＝b1×D1[1][1]+b2×D1[1][0]+b3×D1[0][2]+b4×D1[0][1]；
delta2 rudder deflection angle 2:
Delta2＝b1×D2[1][1]+b2×D2[1][0]+b3×D2[0][2]+b4×D2[0][1]；
delta3 rudder angle 3:
Delta3＝b1×D3[1][1]+b2×D3[1][0]+b3×D3[0][2]+b4×D3[0][1]；
in the formula, b1, b2, b3 and b4 are command control gain parameters, D1, D2 and D3 are interpolation arrays of the pneumatic rudder deflection angle and the airflow attack angle, and the number in brackets in the formula represents the array dimension;
step 4, combining rudder deflection and aerodynamic force to carry out real-time calculation on the rudder effect of the external stores, wherein the method specifically comprises the following steps:
Δ cy: y-direction steering force coefficient rudder effect increment: Δ cy ═ (c1-c2) × Kcy;
Δ cz: z-direction steering force coefficient rudder effect increment: Δ cz ═ (c1+ c2) × Kcz;
Δ cmx: roll moment coefficient rudder effect increment: Δ cmx ═ Kcmx 3;
Δ cmy: yaw moment coefficient rudder effect increment: Δ cmy ═ dcy × (tm-bp);
Δ cmz: pitching moment coefficient rudder effect increment: Δ cmz ═ dcz × (tm-bp);
in the formula, tm is a relative position of a mass center, bp is a relative position of a rudder shaft, Kcy, Kcz and Kcmx are rudder efficiency coefficients, c1 is an interpolation rudder deflection angle of Delta1 rudder deflection angle 1, c2 is an interpolation rudder deflection angle of Delta2 rudder deflection angle 2, and c3 is an interpolation rudder deflection angle of Delta3 rudder deflection angle 3;
step 5, correcting rudder effect iteration track points of the variable-step-length external hanging object, wherein the method specifically comprises the following steps:
cy: and the Y-direction operating force coefficient correction value: cy + Δ Cy;
cz is as follows: z-direction operating force coefficient correction value: cz + Δ Cz;
Cmz: the pitching moment coefficient correction value is as follows: cmz＝Cmz+Δcmz；
Cmx: roll torque coefficient correction value: cmx＝Cmx+Δcmx；
Cmy: roll torque coefficient correction value: cmy＝Cmy+Δcmy；
Wherein, Δ cy: y-direction steering force coefficient rudder effect increment, Δ cz: z-direction steering force coefficient rudder effect increment, delta cmx: roll torque coefficient rudder effect increment, Δ cmy: yaw moment coefficient rudder effect increment, Δ cmz: and increasing the pitching moment coefficient and the rudder effect.
2. The simulation method for capturing the external store control law in the trajectory test according to claim 1, wherein the step 1 is as follows:
f is the trace point instantaneous acceleration: f coe × qs × refS
In the formula, coe is a aerodynamic coefficient, qs is an upper speed pressure at a specified height, and refS is a reference area; alpha _ e is the angle of attack of the store, and the calculation formula is as follows:
in the formula, phiw、θw、ψwThree angular displacements of the plug-in object relative to an air shaft system of the aircraft are obtained;
kkthita _ e is the pitching angle of the external hanging object, namely the included angle between the X axis of the external hanging object and the horizontal plane:
kkthita_e＝θw
psi _ e is the external hanging course angle, namely the included angle between the projection of the X axis of the external hanging in the horizontal plane and the projection of the X axis of the airplane in the horizontal plane:
psi_e＝ψw+β
wherein β is the sideslip angle;
gama _ e is the cross roll angle of the external hanging object, namely the included angle between the longitudinal symmetrical plane of the external hanging object and the vertical plane passing through the X axis of the external hanging object:
gama_e＝φw
dkkthita_e、dpsi_e、dgama_echange rate of pitch angle, change rate of course angle and change rate of roll angle of the outer hanging object:
dkkthita_e＝qEcosφw-rEsinφw
dpsi_e＝(qEsinφw+rEcosφφw)/cosθw
dgama_e＝pE+dpsi_e·sinθw
in the formula, pE、qE、rEIs the projection of the angular velocity of the outer hanging object on three axes of the body axis of the outer hanging object.
3. The simulation method for capturing the plug-in control law in the trajectory test according to claim 1, wherein the pneumatic calculation method in the step 2 is specifically as follows:
cynormal force coefficient:
cztransverse force coefficient:
Cmzpitching moment coefficient:
Cmyyaw moment coefficient:
Cmxroll moment coefficient:
in the formula, Y is a lift force, Z is a transverse force, Mz is a pitching moment, My is a yawing moment, Mx is a rolling moment, b is an average aerodynamic chord length, and l is a wing extension length.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810868862.4A CN109141802B (en) | 2018-08-02 | 2018-08-02 | Simulation method for plug-in control law in capture trajectory test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810868862.4A CN109141802B (en) | 2018-08-02 | 2018-08-02 | Simulation method for plug-in control law in capture trajectory test |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109141802A CN109141802A (en) | 2019-01-04 |
| CN109141802B true CN109141802B (en) | 2020-08-14 |
Family
ID=64799455
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810868862.4A Active CN109141802B (en) | 2018-08-02 | 2018-08-02 | Simulation method for plug-in control law in capture trajectory test |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109141802B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110069842B (en) * | 2019-04-12 | 2023-08-18 | 北京空天技术研究所 | Quick estimation method for rudder efficiency |
| CN110470449A (en) * | 2019-08-23 | 2019-11-19 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of the captive trajectory testing method and test measuring and controlling equipment of continuous control mode |
| CN111707441B (en) * | 2020-06-23 | 2021-04-16 | 重庆大学 | Motion distribution method for main body and separation body decoupling mechanism in linkage track capture experiment |
| CN111693246B (en) * | 2020-06-23 | 2021-04-06 | 中国空气动力研究与发展中心超高速空气动力研究所 | Method for distributing motion of main body and separating body track capture experiment of continuous on-orbit motion |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004020265A (en) * | 2002-06-13 | 2004-01-22 | Kawasaki Heavy Ind Ltd | Method and apparatus for preventing collision in wind tunnel model test device |
| WO2007149983A2 (en) * | 2006-06-22 | 2007-12-27 | Cessna Aircraft Company | Method and system for gathering pressure signature data using a scaled model in a wind tunnel |
| CN104931222A (en) * | 2015-05-04 | 2015-09-23 | 中国航天空气动力技术研究院 | Projectile separation trajectory captive test system |
-
2018
- 2018-08-02 CN CN201810868862.4A patent/CN109141802B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004020265A (en) * | 2002-06-13 | 2004-01-22 | Kawasaki Heavy Ind Ltd | Method and apparatus for preventing collision in wind tunnel model test device |
| WO2007149983A2 (en) * | 2006-06-22 | 2007-12-27 | Cessna Aircraft Company | Method and system for gathering pressure signature data using a scaled model in a wind tunnel |
| CN104931222A (en) * | 2015-05-04 | 2015-09-23 | 中国航天空气动力技术研究院 | Projectile separation trajectory captive test system |
Non-Patent Citations (1)
| Title |
|---|
| 机载制导武器弹射分离安全分析;姜殿民等;《科技信息》;20131231(第5期);全文 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109141802A (en) | 2019-01-04 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109141802B (en) | Simulation method for plug-in control law in capture trajectory test | |
| CN109297666B (en) | Interstage separation wind tunnel test device and test method based on two sets of motion mechanisms | |
| CN110377045B (en) | Aircraft full-profile control method based on anti-interference technology | |
| CN109581892B (en) | Double-turntable semi-physical simulation system and method for full strapdown missile guidance control system | |
| CN110160730B (en) | Device and method for testing separation performance of aircraft plug-in high-speed wind tunnel | |
| CN108152529A (en) | A kind of method based on flight parameter calculation of wind speed and wind direction | |
| CN103926931B (en) | Axial symmetry high-speed aircraft motion feature integrated recognition method | |
| CN110990947A (en) | Multi-field coupling simulation analysis method for launching process of rocket-assisted unmanned aerial vehicle | |
| CN114608794B (en) | Method for measuring aerodynamic coefficient of model wind tunnel virtual flight test | |
| CN109032171B (en) | A kind of control method of the aircraft wind tunnel free-flight based on Nonlinear control law | |
| CN108873929B (en) | Method and system for autonomous landing of fixed-wing aircraft | |
| CN104778376B (en) | A kind of hypersonic gliding bullet Skipping trajectory Forecasting Methodology of near space | |
| CN112558621A (en) | Decoupling control-based flying mechanical arm system | |
| Barrows | Videogrammetric model deformation measurement technique for wind tunnel applications | |
| CN110398339B (en) | Condition determination method for satisfying similarity law of multistage full-free flight wind tunnel test | |
| CN115659523A (en) | Rigid-flexible coupling modeling analysis method for high-aspect-ratio unmanned aerial vehicle | |
| CN110398342B (en) | Method for designing airplane carried object separation wind tunnel free flight test similarity law | |
| CN111008488B (en) | Propeller unmanned aerial vehicle launching process reaction torque modeling method | |
| Song et al. | A wind estimation method for quadrotors using inertial measurement units | |
| CN115097856A (en) | Target tracking dynamic feedback control method for quad-rotor unmanned aerial vehicle based on navigation vector field | |
| Wu et al. | Modeling of small UAV parachute recovery system based on Lagrangian method | |
| CN113607378A (en) | Rope system supporting aircraft model forced free angle motion simulation and suppression method | |
| CN117606737A (en) | Test method for predicting store separation track during rolling maneuver of carrier | |
| CN112947522A (en) | Hard air refueling attitude control method based on finite time observer | |
| CN109634110A (en) | A kind of tailstock formula unmanned plane changeover portion robust control method based on Nonlinear Disturbance Observer |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |