JPH05178294A - Space apparatus control device - Google Patents

Abstract

PURPOSE:To make a space apparatus control device capable of increasing exactitude of judgement about the advisability of launching before launching without requiring previous detailed analysis, and capable of surely coping with a sudden gust of wind whose occurrence is impossible to estimate. CONSTITUTION:The control device 11 of this space apparatus control device consists of a pre-launching preprogrammed-rate resetting part 12, a flight-time preprogrammed-rate resetting part 13 and a control operation part 14. The resetting part 12 sets a pre-launching preprogrammed-rate in a preprogrammed- rate set memory 18 by stored data of a memory 15 and observed data from a wind data observation device 16. The resetting part 13 resets the flight-time preprogrammed-rate based on the data from a wind data observation device 17 and the set memory 18 and outputs it to the control operation part 14. This control operation part 14 computes the correction amount of an attitude based on the preprogrammed-rate from the flight-time preprogrammed-rate resetting part 13 and the airframe attitude information from an inertia sensor 3 and controls the steering angle of an engine.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a space equipment controller having a function of automatically resetting a preprogram rate (posture change amount data) of space equipment based on measured wind data.

[0002]

2. Description of the Related Art Conventionally, a control device for space equipment such as a rocket is constructed as shown in FIG. In FIG. 3, reference numeral 1 denotes a memory that stores an original preprogram rate (posture change amount data).
The pre-program rate read from the controller 2
Entered in. The original stored in the memory 1
The pre-program rate is set so that the stochastic average wind exerts a minimum aerodynamic force (when the angle of attack is almost zero) when it acts on space equipment. In addition, a detection signal is input to the control device 2 from an inertial sensor (IMU) 3 that detects a body attitude. The control device 2 is configured by the control calculation unit 4, and calculates the attitude correction amount from the original preprogram rate from the memory 1 and the actual aircraft attitude information detected by the inertial sensor 3 to control the engine steering angle. The actuator 5 is driven.

The preprogram rate used for the engine steering angle control is set in advance so that the aerodynamic force acting on the space equipment and the engine steering angle are minimized when the stochastic average wind acts. No further changes will be made.

[0004]

In the conventional method of setting the pre-program rate of space equipment with respect to the stochastically averaged wind, the space equipment is launched by actual measurement data 3 to 4 hours before the launch. Since the possibility determination is made in consideration of the wind prediction immediately before the launch, it is necessary to make a determination with a certain margin, and it is difficult to increase the probability of launch.

Further, even in the case of the preliminary analysis, the analysis cost / implementation period cannot be improved because the analysis is performed for all the stochastic winds. Furthermore, even if a system that can continuously observe the wind just before the launch is introduced, there is a problem that the data cannot be reflected.

The present invention has been made in view of the above-mentioned circumstances, does not require a detailed analysis in advance, can increase the accuracy of the propriety determination before launch, and can reliably cope with unpredictable gusts. It is an object of the present invention to provide a space equipment control device that can be used.

[0007]

A space equipment control apparatus according to the present invention observes wind data before launching space equipment.
Wind data observing means, pre-launch preprogram rate resetting means for resetting the original preprogram rate based on the wind data observed by this observing means, and wind just before and during flight of space equipment. Based on the wind data observed by the second wind data observing means, the second wind data observing means for observing the data and the pre-program rate reset by the pre-launch pre-program rate resetting means In-flight preprogramming rate resetting means for further resetting, an inertial sensor for detecting the attitude of the space equipment, and the aircraft attitude detected by the inertial sensor and the in-flight preprogramming rate resetting means. The attitude correction amount is calculated from the calculated pre-program rate, and control calculation means for controlling the engine steering angle is provided. The one in which the features.

[0008]

Before the space equipment is launched, the pre-launch pre-program rate resetting means resets the original pre-program rate based on the final pre-launch wind data observed by the first wind data observing means. To do. Since the pre-program rate set by the pre-launch pre-program rate resetting means is based on the wind data several hours before the launch due to various restrictions, the second pre-program rate is set in order to perform more accurate control. The wind data immediately before the launch observed by the wind data observing means is input to the pre-program rate resetting means during flight, and the pre-program rate is corrected again. Further, even after the launch, the wind data during flight observed by the second wind data observing means is input to the flight pre-program rate resetting means to correct the pre-program rate.

By correcting the preprogram rate based on the wind data observed as described above, the aerodynamic force acting on the space equipment and the generated engine steering angle can be minimized, and a detailed analysis in advance can be performed. Therefore, it is possible to increase the accuracy of the determination as to whether or not to fire before firing.

[0010]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of the present invention will be described below with reference to the drawings.

FIG. 1 is a block diagram showing an embodiment of the present invention. In FIG. 1, reference numeral 11 is a control device, which comprises a pre-launch preprogram rate resetting unit 12, a pre-flight preprogram rate resetting unit 13 and a control calculation unit 14, which are used for the prelaunch preprogram rate resetting unit 12. , Memory 1
Wind data observation device 1 for observing the original preprogram rate and wind data before launch stored in 5
Wind data is input from 6. The original preprogram rate stored in the memory 15 is set so that the stochastic average wind exerts a minimum aerodynamic force (actuator working amount is minimum) when acting on space equipment. .. Observation data is input to the in-flight preprogram rate resetting unit 13 from a wind data observation device 17 for observing wind data during flight.

The pre-launch pre-program rate resetting unit 12 sets the pre-launch pre-program rate based on the pre-program rate from the memory 15 and the wind data from the wind data observing device 16 in the pre-program rate setting memory. Set to 18. The pre-program rate set in the memory 18 is sent to the pre-flight pre-program rate resetting section 13 during flight. The in-flight pre-program rate resetting unit 13 resets the in-flight pre-program rate based on the data from the wind data observation device 17 and the pre-program rate setting memory 18 and outputs it to the control calculation unit 14. To do. The control calculation unit 14 has a function equivalent to that of the conventional control calculation unit 4, and uses the pre-program rate from the flight pre-program rate resetting unit 13 and the attitude correction amount based on the machine attitude information from the inertial sensor 3. Is calculated and the actuator 5 for controlling the engine steering angle is driven.

Next, the operation of the above embodiment will be described. Before launching the space equipment, the pre-launch pre-program rate resetting unit 12 reads the original pre-program rate from the memory 15 and changes the angle of attack according to the final pre-launch wind observed by the wind data observation device 16. Is set to a value such that is almost zero, and is set in the preprogram rate setting memory 18. Then, the data set in the memory 18 is sent to the control device 11, and the pre-program rate is further corrected based on the wind data observed by the wind data observation device 17 immediately before the launch, and when the space device is launched and The engine steering angle during flight is controlled.

The preprogram rate setting memory 1
The data set to 8 is a realistic value as much as it reflects the wind data on the day of launch observed by the wind data observing device 16, and as a result, the aerodynamic force acting on the space equipment becomes small. This is equivalent to the action amount of the actuator 5 being reduced. In this case, the data set in the pre-program rate setting memory 18 is based on the wind data several hours before the launch due to various restrictions, so that the memory 1 can be controlled in order to perform more accurate control.
The pre-during-program of wind data immediately before launch observed by the setting data of 8 and the wind data observation device 17
Input into the rate resetting section 13 and re-program
Modify the rate so that the angle of attack is almost zero. Further, even after the launch, the wind data during flight observed by the wind data observing device 17 is input to the flight pre-program rate resetting section 13 to correct the pre-program rate. Therefore, the space device flies in the atmosphere at the pre-program rate reset by the pre-program rate resetting unit 13 during flight. That is, the control calculation unit 14 determines the action amount of the actuator 5 based on the pre-program rate from the pre-flying program rate resetting unit 13 and the body attitude information from the inertial sensor 3.

The control device 11 for controlling the above-mentioned whole can be replaced by a computer mounted on space equipment, and a ground device (wind data observation device 16) for observing wind data before launch and inputting it to the control device 11. ) Is required, but other verification work can be performed automatically.

Various methods are conceivable for observing wind data immediately before and during flight of space equipment. Figure 2
Wind data observation device 2 installed as ground equipment as shown in
The average wind that does not include the gust component is observed by 1 and the observation data is processed by the data processing device 22 and transmitted to the space equipment 24 through the data transmitting device 23. The wind data observation device 21 and the data processing device 22 are several minutes to
The wind data can be accurately observed and processed up to an altitude of about 30 km in about 10 minutes.
3 is capable of transmitting the observation data to the space equipment 24 in real time. On the other hand, the space equipment 24 is provided with a wind data observation device 25 for observing / predicting a local gust component and a processing device 26 for processing the observation data, and the observation transmitted from the ground device via the data transmission device 23. The data and the data observed by the wind data observation device 25 are combined by the processing device 26 and input as wind data to the flight pre-program rate resetting unit 13 in FIG.

When the above-mentioned ground equipment shown in FIG. 2 is not used, the wind data observation device 17 shown in FIG. Can be done.

[0018]

As described above in detail, according to the present invention, the preprogram rate is reset based on the wind data observed immediately before the launch of space equipment and the wind data observed during flight. Therefore, the aerodynamic force acting on the space equipment and the generated engine steering angle can always be minimized, and therefore, the accuracy of the launch approval / disapproval determination before the launch can be increased without performing a detailed analysis in advance in the control system. , It can reliably respond to unpredictable gusts,
In addition, the payload weight can be increased. Also,
There is a high probability that a mission that is impossible with a conventional controller will be possible.

[Brief description of drawings]

FIG. 1 is a block diagram showing a configuration of a space device control apparatus according to an embodiment of the present invention.

FIG. 2 is a block diagram showing a configuration example of an observation device for wind data during flight.

FIG. 3 is a block diagram showing a configuration of a conventional space equipment control device.

[Explanation of symbols]

11 ... Control device, 12 ... Pre-program pre-program rate resetting unit, 13 ... Flight pre-program rate resetting unit, 14 ... Control calculation unit, 15 ... Memory, 16 ... Wind data observation device, 17 ... Wind data Observation device, 18 ... Preprogram rate setting memory, 21 ... Wind data observation device, 2
2 ... Data processing device, 23 ... Data transmission device, 24 ... Space equipment, 25 ... Wind data observation device, 26 ... Processing device.

Claims (1)

[Claims] 1. A first wind data observation means for observing wind data before launching a space device, and an original preprogram based on the wind data observed by this observation means.
The pre-launch preprogram rate resetting means for resetting the rate, the second wind data observing means for observing the wind data immediately before and during the flight of the space equipment, and the prelaunch preprogram rate resetting means. In-flight preprogram rate resetting means for further resetting the reset preprogram rate based on the wind data observed by the second wind data observing means, and inertia for detecting the attitude of the space equipment. A sensor, a control calculation means for calculating an attitude correction amount from the airframe attitude detected by the inertial sensor and the preprogram rate reset by the pre-program rate resetting means during flight, and controlling the engine steering angle; A space equipment control device comprising: