CN116294824A - Design method of training target drone - Google Patents
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41J—TARGETS; TARGET RANGES; BULLET CATCHERS
- F41J9/00—Moving targets, i.e. moving when fired at
- F41J9/08—Airborne targets, e.g. drones, kites, balloons
- F41J9/10—Airborne targets, e.g. drones, kites, balloons towed
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
- B64C39/024—Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
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- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
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Abstract
The invention discloses a design method of a training target drone, which aims at realizing the closed-loop active control of stall-passing asymmetric flow by adopting a synthetic double-jet exciter, and aims at realizing the self-adaptive control and the proportional control of the synthetic double-jet exciter to the asymmetric lateral force of an aircraft under a large attack angle by taking a wind tunnel dynamic experiment technology, a flow field display technology and a dynamic data test technology as means based on theoretical analysis and numerical simulation results; verifying the closed-loop control efficiency of the designed precursor vortex active control exciter through a stall passing flight wind tunnel experiment; the method is characterized in that the structure improvement is carried out by adopting a current mature model machine to serve as a structural foundation of a training target machine, and meanwhile, the characteristics of generalization, serialization and the like are considered, and mature products are adopted for integrated design on product materials, internal circuits, steering engines and flight control systems; meanwhile, the method is innovated in the aspects of ground control system and software, unmanned aerial vehicle navigation, engine, oil circuit system, target characteristic simulation and the like.
Description
Technical Field
The invention relates to unmanned aerial vehicle design technology, in particular to a design method of a training target drone.
Background
The pneumatic appearance design of the training target aircraft takes the pneumatic appearance of the existing F16C aircraft as a reference template, and is designed strictly according to the 1:4.6 reduction ratio of the appearance structure of the F16C. In the primary stage, the current mature model machine is adopted to carry out structural improvement to serve as a structural foundation of the training target machine, and meanwhile, characteristics of generalization, serialization and the like are considered, and mature products are adopted to carry out integrated design on product materials, internal circuits, steering engines and flight control systems; meanwhile, the method is innovated in the ground control system, software, unmanned aerial vehicle navigation, engine, oil circuit system, target characteristic simulation and other contents, has higher technical reserve and product research and development manufacturing capacity in the field, and particularly forms the field of professional direction in the ground control, unmanned aerial vehicle navigation and target characteristic simulation technology, so as to master the core technology of the target drone; can flower around the target plane technology at multiple points in multiple fields.
Training the target machine requires:
the vehicle has excellent flying performance and strong medium-low altitude transonic maneuver performance. The wing body fusion body has the main advantages of reducing wave drag, improving lift-drag ratio and transonic flutter boundary, enhancing rigidity, enabling the aircraft to have good maneuverability, increasing internal space and reducing aircraft weight; the strake wings with large sweepback angle and sharp front edge are installed along the front fuselage, and controllable vortex is provided at the connection part of the wings and the fuselage, so that the boundary layers can be kept not to be separated even at a large attack angle, and the lift force and stability are improved. The front edge motor-driven flap, the wing section of the wing has variable camber, and the lift-drag ratio can be improved in continuous large overload turning.
Relaxing the static stability, adopting the technology of relaxing the static stability, i.e. relaxing the strict limit on the static stability, the pneumatic center can be very close to the gravity center, can also be coincident, and is even in front of the gravity center. The static stability of the aircraft becomes extremely small or unstable, so that the static stability of the aircraft is a negative value during low-speed flight, and the control surface is automatically controlled by a stabilizing system during flight, so that stable flight is ensured; at high speeds, the static stability of the aircraft is only positive. The advantage of this is that the tail size can be reduced, the structural weight and resistance can be reduced, and the maneuverability and maneuverability of the aircraft can be improved.
For the model machine, the design method of the training target machine in the prior art does not have generalization and serialization, and meanwhile, integrated design is not adopted on product materials, internal circuits, steering engines and flight control systems, so that the design is complex and the simulation performance is poor.
In view of this, the present invention has been made.
Disclosure of Invention
The invention aims to provide a design method of a training target drone, which aims to solve the technical problems in the prior art.
The invention aims at realizing the following technical scheme:
the design method of the training target machine comprises the following steps:
firstly, the purpose of realizing the over-stall asymmetric flow closed-loop active control by adopting a synthetic double-jet exciter is to realize the self-adaptive control and the proportional control of the synthetic double-jet exciter to the asymmetric lateral force of the aircraft under a large attack angle by taking a wind tunnel dynamic experiment technology, a flow field display technology and a dynamic data test technology as means based on theoretical analysis and numerical simulation results;
and then, verifying the closed-loop control efficiency of the designed precursor vortex active control exciter through a overspeed flight wind tunnel experiment, and completing the design method of the training target drone according to the verification result.
Compared with the prior art, the design method of the training target machine adopts the current mature model machine to carry out structural improvement as the structural basis of the training target machine, and simultaneously considers the characteristics of generalization, serialization and the like, and adopts mature products on product materials, internal circuits, steering engines and flight control systems to carry out integrated design; meanwhile, the method is innovated in the aspects of ground control system and software, unmanned aerial vehicle navigation, engine, oil circuit system, target characteristic simulation and the like.
Drawings
Fig. 1 is a schematic structural diagram of a training target machine according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of strain gage arrangement at a location associated with an empennage mounting bracket according to an embodiment of the present invention;
FIG. 3 is a schematic view of an arrangement of strain gauges at relevant portions of an engine mount according to an embodiment of the present invention;
FIG. 4 is a diagram showing a combined measurement design of the angle of attack and sideslip angle according to an embodiment of the present invention.
In the figure:
1-airspeed tube, 2-fairing, 3-instrument cabin, recovery umbrella cabin, 4-flight control system, power supply system, 5-aileron (flap), 6-fuselage (containing oil tank, landing gear, etc. inside), 7-rudder, 8-engine and jet pipe, 9-full-motion horizontal tail, 10-air inlet channel;
11. tail wing, 12, engine, 13 to 15, strain gage.
Detailed Description
The technical solutions in the embodiments of the present invention are clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention; it will be apparent that the described embodiments are only some embodiments of the invention, but not all embodiments, which do not constitute limitations of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to fall within the scope of the invention.
The terms that may be used herein will first be described as follows:
the term "and/or" is intended to mean that either or both may be implemented, e.g., X and/or Y are intended to include both the cases of "X" or "Y" and the cases of "X and Y".
The terms "comprises," "comprising," "includes," "including," "has," "having" or other similar referents are to be construed to cover a non-exclusive inclusion. For example: including a particular feature (e.g., a starting material, component, ingredient, carrier, formulation, material, dimension, part, means, mechanism, apparatus, step, procedure, method, reaction condition, processing condition, parameter, algorithm, signal, data, product or article of manufacture, etc.), should be construed as including not only a particular feature but also other features known in the art that are not explicitly recited.
The term "consisting of … …" is meant to exclude any technical feature element not explicitly listed. If such term is used in a claim, the term will cause the claim to be closed, such that it does not include technical features other than those specifically listed, except for conventional impurities associated therewith. If the term is intended to appear in only a clause of a claim, it is intended to limit only the elements explicitly recited in that clause, and the elements recited in other clauses are not excluded from the overall claim.
Unless specifically stated or limited otherwise, the terms "mounted," "connected," "secured," and the like should be construed broadly to include, for example: the connecting device can be fixedly connected, detachably connected or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the terms herein above will be understood by those of ordinary skill in the art as the case may be.
The terms "center," "longitudinal," "transverse," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," etc. refer to an orientation or positional relationship based on that shown in the drawings, merely for ease of description and to simplify the description, and do not explicitly or implicitly indicate that the apparatus or element in question must have a particular orientation, be constructed and operated in a particular orientation, and therefore should not be construed as limiting the present disclosure.
What is not described in detail in the embodiments of the present invention belongs to the prior art known to those skilled in the art. The specific conditions are not noted in the examples of the present invention and are carried out according to the conditions conventional in the art or suggested by the manufacturer. The reagents or apparatus used in the examples of the present invention were conventional products commercially available without the manufacturer's knowledge.
The design method of the training target machine comprises the following steps:
firstly, the purpose of realizing the over-stall asymmetric flow closed-loop active control by adopting a synthetic double-jet exciter is to realize the self-adaptive control and the proportional control of the synthetic double-jet exciter to the asymmetric lateral force of the aircraft under a large attack angle by taking a wind tunnel dynamic experiment technology, a flow field display technology and a dynamic data test technology as means based on theoretical analysis and numerical simulation results;
and then, verifying the closed-loop control efficiency of the designed precursor vortex active control exciter through a overspeed flight wind tunnel experiment, and completing the design method of the training target drone according to the verification result.
Taking the variation of the flow characteristic of the aircraft model as a feedback signal, designing a self-adaptive closed-loop active control system based on a synthetic double-jet exciter to realize self-adaptive elimination control of asymmetric lateral force in a rapid maneuvering process;
the two jet intensities are controlled by changing the working parameters of the exciter, the proportional control capability of asymmetric lateral force is verified, and a control rule is obtained.
From the viewpoints of weight, performance, modification complexity, reliability and the like, the axisymmetric vectoring nozzle is selected, the good aerodynamic performance of the axisymmetric convergent-divergent nozzle is reserved, and the function of the expansion section is structurally expanded, so that supersonic airflow can be generated, and the airflow direction can be deflected according to the requirements of an airplane.
And strain gauges are arranged at the relevant positions of the steering engine mounting frame and the engine mounting frame, two forces and one moment of the pneumatic control surface acting on the aircraft body are calculated through the measured values of the strain gauges, and the engine and the thrust vector of the engine act on three forces and three moments of the aircraft body.
The flight parameters of the aircraft are accurately measured by adopting a high-precision combined measurement method, and aerodynamic parameters including an attack angle and a sideslip angle are obtained through the scaled aircraft.
Active radar equipment is added on the target plane, and the threat of different types of real targets is simulated by replacing the antenna form and the configuration part of the antenna form according to the requirement.
The airborne threat targets include radiation and reflection of the skin, flight conditions and environment, infrared radiation of the jet engine;
for infrared radiation of jet engine which plays a main role, when the infrared characteristic is simulated and estimated, the infrared radiation intensity of the engine of the simulated target is used as a basis, and on the basis of estimating the infrared radiation of the target aircraft, the required infrared characteristic is met by adding a corresponding infrared radiation source, wherein the infrared radiation source comprises a drag pipe and an infrared bullet.
Aiming at the characteristics of multiple types of threat targets in the air, the characteristics of multiple types of targets and different performance indexes are utilized, and the targets with different dynamic performances are simulated in a specified time domain, space domain and speed domain by a flight path planning method, so that the simulation of multi-target threat in the air is formed.
In summary, according to the design method of the training target machine, the structure improvement is carried out by adopting the current mature model machine to serve as the structural foundation of the training target machine, and meanwhile, the characteristics of generalization, serialization and the like are considered, so that the integrated design is carried out on the product materials, the internal circuits, the steering engine and the flight control system by adopting mature products; meanwhile, the method is innovated in the aspects of ground control system and software, unmanned aerial vehicle navigation, engine, oil circuit system, target characteristic simulation and the like.
The design method of the training target drone is important to consider aspects of specialization, generalization, modularization, serialization and the like of a system in system design.
(1) Specialization of
The specialized requirements of the training target drone are focused on the technical characteristics of unmanned aerial vehicles, and the specialization of products in the design, manufacture, assembly and use of unmanned aerial vehicles, especially unmanned target drones, is highlighted; the method and the device can continuously improve the relevant technical knowledge reserve of the unmanned aerial vehicle, provide the professional skills of technicians, flexibly apply the professional skills to realize better and faster meeting of customer demands in front of the continuously changing market, and improve the speed of product retrofit.
(2) Universalization
The project needs to be demonstrated and planned in detail at the beginning of design in generalization, and the product has the general purpose of a generalized system in product structure, general purpose of electric composition, general purpose of control and navigation and general purpose of use operation; product universalization is intended to reduce the consumption of people, money, and things due to excessive design and requirements related to the product model.
(3) Modular system
The product mainly used for integration has high requirements on modularized design, and the functions of the product are modularized and divided according to the structural composition of the target aircraft, so that the module has the characteristics of high integration level, simple and clear interface between the modules, convenience in installation, compact module structure, standard design and the like.
(4) Serialization
The training target machine forms serialization on the product composition and model planning according to different customer demands in the future, and meets different use requirements.
The composition diagram of the training target machine system is shown in fig. 1, and an instrument hatch cover is in a bubble shape and is used for placing the contents of a main power switch of the target machine system, a target machine system detection interface, a high-definition camera installation interface and the like; for target characterization, the target may be mounted Long Baqiu on the fairing position, on the aileron and outside the fuselage, or an infrared light source, as desired.
The control system adopts four-redundancy fly-by-wire technology and mainly comprises a signal conversion device, a flight control computer, a cable and an action device. The core module used as the flight control of the target aircraft bears the real-time control of the whole flight process of the target aircraft and communicates with the ground control station in real time.
The shell is of a semi-hard shell structure, and the design of the aileron fusion body is adopted, so that the fuselage and the wings are smoothly connected, not only can the flight resistance be reduced and the lift-drag ratio be improved, but also the structural strength is beneficial. The tail part is provided with a full-moving type horizontal tail, the plane shape of the full-moving type horizontal tail is similar to that of a wing, and the rear part of a wing root fairing is provided with a cracking type speed reducer. The vertical tail is higher, the stabilizer is large, and the trailing edge is a full span rudder. The landing gear is a retractable front three-point structure landing gear.
In order to more clearly demonstrate the technical scheme and the technical effects provided by the invention, the following detailed description of the embodiments of the invention is given by way of specific examples.
Example 1
As shown in fig. 1 to 4:
1. asymmetric vortex control device and control system
The invention adopts a synthetic double-jet exciter to realize the over-stall asymmetric flow closed-loop active control, uses the means of wind tunnel dynamic experiment technology, flow field display technology, dynamic data test technology and the like based on theoretical analysis and numerical simulation results to realize the self-adaptive control and the proportional control of the synthetic double-jet exciter to the asymmetric lateral force of the aircraft under a large attack angle, and verifies the closed-loop control efficiency of the designed precursor vortex active control exciter through an over-stall flight wind tunnel experiment.
The invention takes the variable quantity of the flow characteristic of the aircraft model as a feedback signal, designs a self-adaptive closed-loop active control system based on a synthetic double-jet exciter, and realizes the self-adaptive elimination control of asymmetric lateral force in the rapid maneuvering process; the two jet intensities are controlled by changing the working parameters of the exciter, the proportional control capability of asymmetric lateral force is verified, and a control rule is obtained.
2. Scaled thrust vector and control system
The invention selects axisymmetric vector jet pipe (AVEN) from the angles of weight, performance, refitting complexity and reliability, and the like, and is mainly characterized in that the invention fully maintains the good pneumatic performance of axisymmetric convergent-divergent jet pipe, and only structurally expands the function of the expansion section, so that the invention can generate supersonic air flow and deflect the air flow direction according to the airplane requirement.
The invention aims to reduce the interference effect of vector jet flow on the flow field of the airplane as much as possible, and the vector rotation angle, the pneumatic area and the air flow speed of the thrust vector engine can be accurately controlled. For axisymmetric vectoring nozzles, the precise control parameters of the engine vectoring nozzle mechanism are obtained by controlling the steering control ring to precisely realize the area and the vectoring angle.
The inverse solution control law of the axisymmetric vectoring nozzle and the research of the analytic expression thereof are the design basis of a vectoring engine control system and the research and design basis of the problems of maneuverability, aerodynamic control and the like of an airplane with a vectoring engine. The difficulty is that it determines the input parameters not by giving the pose of a certain executing member in space, but by giving the position of a time-varying geometry made up of a series of members in space. The object controlled by inverse solution has complex structure and difficult motion analysis; the design parameters are more, and the mathematical model is complex; the real-time performance of solving is also high, so that the model is simplified to be easy to solve on the premise that the accuracy is not changed as much as possible in the calculation of inverse solution control.
Because the vector deflection section of the axisymmetric vector spray pipe is formed by enveloping a series of expansion regulating plates and sealing plates thereof, the key of motion inverse solution is to determine the spatial distribution rule of the expansion regulating plates when given vector rotation angles and areas, further calculate the pose of the corresponding A9 steering control ring, and finally calculate the displacement output function of the A9 ring driving actuator.
3. Aerodynamic force data acquisition based on scaling model flight test
(1) Principle of obtaining aerodynamic parameters in a scaled aircraft flight test:
the aircraft dynamics equation comprises aircraft inertia force, aerodynamic force, a pneumatic control surface and a power system control force, the aircraft inertia force is obtained by measuring acceleration and angular acceleration of a model aircraft in the flight process, and the aerodynamic force of a certain flight state of the model aircraft can be calculated by measuring the pneumatic control surface and the power system control force acting on the aircraft body through a force sensor. Aerodynamic force parameters of the aircraft can be calculated by combining aerodynamic forces measured in different flight states.
(2) Method for measuring control force of pneumatic control surface and power system
In order to measure the control force of the pneumatic control surface and the power system of the airplane on the airplane, the force sensor needs to be arranged between the pneumatic control surface and the power system and the airplane, and the force sensor needs to have the characteristics of accurate measurement and light weight.
The invention provides a method for arranging strain gauges at the relevant positions of a steering engine mounting frame and an engine mounting frame, wherein two forces and one moment of a pneumatic control surface acting on an aircraft body are calculated through the measured values of the strain gauges, and an engine and a thrust vector thereof act on three forces and three moments of the aircraft body.
And arranging strain gauges at the relevant parts of the pneumatic control surface and the engine mounting frame to form a force sensor.
4. High-precision combined measurement system
According to the invention, the aerodynamic parameters are acquired by the scaling aircraft, so that the flight parameters of the aircraft are required to be accurately measured, and the measurement accuracy of the measurement sensors can be improved by the high-accuracy combined measurement method. The attack angle and the sideslip angle are extremely important two quantities in flight state parameters, and the relationship between airspeed and the axis of the aircraft body is measured, so that the method has important significance for accurately measuring the airspeed in real time. ADS (including FADS) is independently used to obtain an attack angle and a sideslip angle, so that the stability is high for a long time, the medium-low frequency response is good, but the characteristics of poor dynamic performance and large measurement noise exist; SINS is used alone to calculate the attack angle and sideslip angle, and the dynamic performance is good, but the accuracy is higher only in a short time due to the existence of inherent errors such as gyro drift and the like.
It is readily apparent that the signals from these two approaches are complementary and can therefore be fused by complementary filtering methods, and the measurement system thus formed is a combined system, as shown in fig. 4.
5. Scaled aircraft platform capable of measuring motion and pneumatic parameters simultaneously
The aircraft motion parameters comprise three directions of speed, angular speed, acceleration angle, acceleration, flight attack angle and sideslip angle, the speed, angular speed, acceleration and angular acceleration data can be measured by installing a GPS sensor, an accelerometer and a gyroscope in an aircraft model, the flight attack angle and sideslip angle data can be measured by an atmosphere data system, the aerodynamic control surface control moment can be measured by installing a force and moment sensor between the aerodynamic control surface and an aircraft body, and the thrust and the control moment of the engine and the thrust vector thereof can be measured by installing a force and moment sensor between the engine and the aircraft body.
The vector deflection section of the axisymmetric vector spray pipe is formed by enveloping a series of expansion regulating plates and sealing plates thereof, so that the key of motion inverse solution is to determine the spatial distribution rule of the expansion regulating plates when given vector rotation angles and areas are determined, further obtain the pose of a corresponding A9 steering control ring, and finally obtain the displacement output function of an A9 ring driving actuator cylinder.
The aircraft motion parameters comprise three directions of speed, angular velocity, acceleration angle, acceleration, flying attack angle and sideslip angle, the speed, the angular velocity, the acceleration and the angular acceleration data can be measured by installing a GPS sensor, an accelerometer and a gyroscope in an aircraft model, the flying attack angle and sideslip angle data can be measured by an atmosphere data system, the operating moment of the pneumatic control surface can be measured by installing a force and moment sensor between the pneumatic control surface and an aircraft body, and the thrust and the operating moment of the engine and the thrust vector thereof can be measured by installing a force and moment sensor between the engine and the aircraft body.
For airborne threat targets, infrared radiation from jet engines is a major contributor, although factors affecting their infrared properties, such as skin radiation and reflection, flight status and environment, etc. In the simulation and estimation of infrared characteristics, the infrared radiation intensity (including skin radiation) of an engine of a simulated target is based on. On the basis of estimating the infrared radiation of the target machine, the required infrared characteristics are met by adding a corresponding infrared radiation source (such as a drag pipe, an infrared bomb and the like) of '1'.
The flight path planning is to plan a flyable path from a starting point to an end point on the basis of considering target aircraft performance and task requirements. The generated flight path is usually formed by connecting a series of straight curves end to end, and can be specifically described as: start point, constraints to be obeyed, dynamic performance and target area to be simulated, threat or obstacle area, end point. In the flight path planning, factors to be considered include:
minimum step size: minimum straight flight distance before each turn;
maximum turning angle: due to the limitation of overload, the target aircraft can only turn within a range equal to or smaller than the maximum turning angle;
track length: the distance the drone flies is limited by fuel and time of flight ration;
the necessary flying spot: some positions that the drone must go through when performing the simulation task;
the fixed angle approaches the target: for threat needs of the path shortcuts, the drone must approach the target at a set angle;
threat: the corresponding threat source types and other limitations are considered in the flight process of the target aircraft.
The multi-machine coordinated flight path planning is a main characteristic of simulating the movement characteristics of a target by using target machines, and when establishing a flight path of each target machine, it is very important that each target machine reaches a preset airspace on time except for preventing an air collision accident. For this purpose, firstly, the take-off place of the target aircraft is selected and the flying speed of the target aircraft is coordinated; and secondly, correcting the flight path and adjusting the distance of the target drone to the target area.
The foregoing is only a preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present invention should be included in the scope of the present invention. Therefore, the protection scope of the present invention should be subject to the protection scope of the claims. The information disclosed in the background section herein is only for enhancement of understanding of the general background of the invention and is not to be taken as an admission or any form of suggestion that this information forms the prior art already known to those of ordinary skill in the art.
Claims (8)
1. A method of designing a training target comprising:
firstly, the purpose of realizing the over-stall asymmetric flow closed-loop active control by adopting a synthetic double-jet exciter is to realize the self-adaptive control and the proportional control of the synthetic double-jet exciter to the asymmetric lateral force of the aircraft under a large attack angle by taking a wind tunnel dynamic experiment technology, a flow field display technology and a dynamic data test technology as means based on theoretical analysis and numerical simulation results;
and then, verifying the closed-loop control efficiency of the designed precursor vortex active control exciter through a overspeed flight wind tunnel experiment, and completing the design method of the training target drone according to the verification result.
2. The method of designing a training target as claimed in claim 1, wherein:
taking the variation of the flow characteristic of the aircraft model as a feedback signal, designing a self-adaptive closed-loop active control system based on a synthetic double-jet exciter to realize self-adaptive elimination control of asymmetric lateral force in a rapid maneuvering process;
the two jet intensities are controlled by changing the working parameters of the exciter, the proportional control capability of asymmetric lateral force is verified, and a control rule is obtained.
3. The method of designing a training target as claimed in claim 2, wherein:
from the viewpoints of weight, performance, modification complexity, reliability and the like, the axisymmetric vectoring nozzle is selected, the good aerodynamic performance of the axisymmetric convergent-divergent nozzle is reserved, and the function of the expansion section is structurally expanded, so that supersonic airflow can be generated, and the airflow direction can be deflected according to the requirements of an airplane.
4. A method of designing a training target as claimed in claim 3, wherein:
and strain gauges are arranged at the relevant positions of the steering engine mounting frame and the engine mounting frame, two forces and one moment of the pneumatic control surface acting on the aircraft body are calculated through the measured values of the strain gauges, and the engine and the thrust vector of the engine act on three forces and three moments of the aircraft body.
5. The method of claim 4, wherein the high-precision combined measurement method is used to accurately measure the flight parameters of the aircraft and the aerodynamic parameters, including the angle of attack and sideslip angle, are obtained by scaling the aircraft.
6. The method of claim 5, wherein the target aircraft is provided with an active radar device to simulate the threat of different types of real targets by changing the antenna pattern and its configuration as needed.
7. The method of claim 6, wherein the air threat objects include skin radiation and reflection, flight status and environment, jet engine infrared radiation;
for infrared radiation of jet engine which plays a main role, when the infrared characteristic is simulated and estimated, the infrared radiation intensity of the engine of the simulated target is used as a basis, and on the basis of estimating the infrared radiation of the target aircraft, the required infrared characteristic is met by adding a corresponding infrared radiation source, wherein the infrared radiation source comprises a drag pipe and an infrared bullet.
8. The method according to claim 7, wherein the target aircraft with different dynamic performances simulate the required threat targets in the specified time domain, space domain and speed domain by utilizing the characteristics of multiple models and different performance indexes of the target aircraft aiming at multiple types of threat targets in the air, and further simulate the multi-target threat in the air.
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| CN202310069299.5A CN116294824A (en) | 2023-02-06 | 2023-02-06 | Design method of training target drone |
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