A transonic guidance control method with multi-objective parameter constraints

Abstract

A multi-objective parameter-constrained transonic guidance and control method addresses the issue of transonic delivery separation point control accuracy, achieving high velocity control accuracy while ensuring high-precision position control. This method integrates a proportional guidance method with angle-of-fall constraints and a velocity control method, leveraging the strengths of both approaches. Velocity control is introduced as a supplementary control measure through a threshold determination method to minimize its impact on position control accuracy. This improved method, based on a proven method, demonstrates strong feasibility.

Description

Technical Field

[0001] The invention relates to a multi-objective parameter-constrained transonic guidance control method, belonging to the technical field of control. Background Art

[0002] When a high-speed aircraft is used as a delivery platform, the payload can be delivered by parachute drag. In order to adapt to the use requirements of the parachute and the working requirements of the payload, the parachute needs to be opened at subsonic speed, and the position, altitude, speed and other parameters need to be precisely controlled.

[0003] High-speed aircraft flying at supersonic speeds are advantageous for long-range payload delivery. To deploy the parachute at subsonic speeds, significant deceleration is required before reaching the delivery separation point. Due to the large aerodynamic prediction deviations during the subsonic phase, parachute deployment should be avoided, placing strict constraints on speed control. Furthermore, the parachute drag process exhibits significant error dispersion, necessitating the utmost precision in controlling parameters such as the delivery point's position, altitude, and velocity, placing significant constraints on the guidance and control system. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to overcome the deficiencies of the prior art and solve the problem of precise control of the separation point of transonic delivery.

[0005] The purpose of the present invention is achieved through the following technical solutions:

[0006] A multi-objective parameter-constrained transonic guidance control method, comprising:

[0007] Use the following formula to determine the required velocity direction change rate of pitch Yaw requires the rate of change of velocity direction

[0008]

[0009] where K GD , K LD , K GT , K LT is the design parameter, is the pitch and yaw line of sight angular rate, λ D ,λ T is the pitch and yaw sight angle, γ DF , γ TF are the target inclination and deflection values, T g To predict the remaining time;

[0010] use Calculate the inclination change rate as follows: Declination rate of change

[0011]

[0012]

[0013] where σ T is the deflection angle;

[0014] use Calculate the normal overload instruction n as follows: y , lateral overload instruction n z

[0015]

[0016]

[0017] where θ T is the inclination angle, g is the acceleration of gravity, and r is the length of the earth's center radius;

[0018] The current speed V corresponding to the current target distance R is compared with the nominal speed V corresponding to the target distance R bound before flight. ref Perform difference calculation; when VV ref ≥ΔV max When the normal overload instruction is corrected to n y +k(VV ref ); otherwise, the normal overload instruction is not corrected; where ΔV max , k are setting parameters.

[0019] In one embodiment of the present invention, the guidance control method is used to simultaneously improve speed and position control accuracy.

[0020] Compared with the prior art, the present invention has the following beneficial effects:

[0021] (1) Aiming at the problem of control accuracy of the separation point of transonic delivery, a higher speed control accuracy is achieved on the basis of ensuring high-precision position control.

[0022] (2) The proportional guidance method with landing angle constraint and the speed control method are integrated to fully utilize the advantages of the two methods.

[0023] (3) Speed control is introduced as a supplementary control method through the determination threshold to minimize the impact on position control accuracy.

[0024] (4) Improvements are made based on mature methods, and the method is more feasible. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 Flow chart of the steps of the method of the present invention. DETAILED DESCRIPTION

[0026] To make the objectives, technical solutions and advantages of the present invention more clear, the embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.

[0027] Example 1:

[0028] A multi-objective parameter-constrained transonic guidance control method, such as Figure 1 Shown, including:

[0029] Step 1: Calculate the overload instruction using the proportional guidance method with landing angle constraint

[0030] According to formula (1), the required velocity direction change rate of pitch is calculated Yaw requires the rate of change of velocity direction

[0031]

[0032] where K GD , K LD , K GT , K LT is the design parameter, is the pitch and yaw line of sight angular rate, λ D ,λ T is the pitch and yaw sight angle, γ DF , γ TF are the target inclination and deflection values, T g To predict the remaining time.

[0033] Calculate the inclination change rate according to formula (2): Declination rate of change

[0034]

[0035]

[0036] where σ T is the deflection angle.

[0037] According to formula (3), the normal overload instruction n is calculated y , lateral overload instruction n z .

[0038]

[0039]

[0040] where θ T is the inclination angle, g is the acceleration due to gravity, and r is the length of the Earth's center radius.

[0041] Step 2: Use speed control method to correct the overload instruction

[0042] The current speed V corresponding to the current target distance R is compared with the nominal speed V corresponding to the target distance R bound before flight. ref Perform difference calculation. When VV ref ≥ΔV max When the normal overload instruction is corrected to n y +k(VV ref ); otherwise, the normal overload instruction is not corrected. max , k are setting parameters.

[0043] Example 2:

[0044] A delivery method based on the guidance and control method described in Example 1, comprising:

[0045] The high-speed aircraft adopts the guidance and control method to perform deceleration control, and delivers the payload after entering the subsonic range.

[0046] In this process, the payload is separated from the high-speed aircraft by parachute dragging.

[0047] Example 3:

[0048] A high-speed aircraft using the guidance and control method described in Example 1, wherein the high-speed aircraft carries a payload;

[0049] In this process, the payload is separated from the high-speed aircraft by parachute dragging.

[0050] Example 4:

[0051] A payload delivered in the subsonic range, carried by a high-speed aircraft;

[0052] The high-speed aircraft adopts the guidance and control method described in Example 1 to perform deceleration control, and after entering the subsonic range, the payload is delivered.

[0053] In this process, the payload is separated from the high-speed aircraft by parachute dragging.

[0054] Example 5:

[0055] An electronic device, comprising:

[0056] processor; and

[0057] a memory for storing computer program instructions;

[0058] When the computer program instructions are loaded and run by the processor, the processor executes the guidance control method described in Example 1.

[0059] Example 6:

[0060] A computer-readable storage medium stores computer program instructions, which, when loaded and executed by a processor, cause the processor to execute the guidance control method described in Example 1.

[0061] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

[0062] Although the present invention has been disclosed above in terms of preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solutions of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the scope of protection of the technical solutions of the present invention.

Claims

1. A multi-objective parameter-constrained transonic guidance control method, characterized in that: include: Use the following formula to determine the required velocity direction change rate of pitch Yaw requires the rate of change of velocity direction where K GD , K LD , K GT , K LT is the design parameter, is the pitch and yaw line of sight angular rate, λ D ,λ T is the pitch and yaw sight angle, γ DF , γ TF are the target inclination and deflection values, T g To predict the remaining time; use Calculate the inclination change rate as follows: Declination rate of change where σ T is the deflection angle; use Calculate the normal overload instruction n as follows: y , lateral overload instruction n z where θ T is the inclination angle, g is the acceleration of gravity, and r is the length of the earth's center radius; The current speed V corresponding to the current target distance R is compared with the nominal speed V corresponding to the target distance R bound before flight. ref Perform difference calculation; when VV ref ≥ΔV max When the normal overload instruction is corrected to n y +k(VV ref ); otherwise, the normal overload instruction is not corrected; where ΔV max , k are setting parameters.

2. The guidance control method according to claim 1, characterized in that: This guidance control method is used to improve both speed and position control accuracy.

3. A delivery method based on the guidance and control method according to claim 1 or 2, characterized in that: include: The high-speed aircraft adopts the guidance and control method to perform deceleration control, and delivers the payload after entering the subsonic range.

4. The delivery method according to claim 3, characterized in that: The payload is separated from the high-speed aircraft by parachute.

5. A high-speed aircraft using the guidance and control method according to claim 1 or 2, characterized in that: The high-speed aircraft carries a payload; The high-speed aircraft adopts the guidance and control method to perform deceleration control, and delivers the payload after entering the subsonic range.

6. The high-speed aircraft according to claim 5, characterized in that: The payload is separated from the high-speed aircraft by parachute.

7. A payload delivered in the subsonic range, characterized in that: The payload is carried by a high-speed aircraft; The high-speed aircraft adopts the guidance and control method described in claim 1 or 2 to perform deceleration control, and the payload is delivered after entering the subsonic range.

8. The load according to claim 7, characterized in that The payload is separated from the high-speed aircraft by parachute.

9. An electronic device comprising: processor; as well as a memory for storing computer program instructions; When the computer program instructions are loaded and executed by the processor, the processor executes the guidance control method according to claim 1 or 2.

10. A computer-readable storage medium having computer program instructions stored thereon, wherein when the computer program instructions are loaded and executed by a processor, the processor is caused to execute the guidance control method according to claim 1 or 2.

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