JP2792322B2 - Transmission power control type control system - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention is used for ground control stations such as a rocket launch control system and a polar orbit satellite tracking control system, and controls the transmission power of a control command wave in accordance with the position and distance of an air vehicle. The present invention relates to a transmission power control type control system.

[0002]

2. Description of the Related Art Ground control stations such as a conventional rocket launch control system and a polar orbit satellite tracking control system track a rocket or a satellite and transmit a control command wave through a parabolic antenna. In this case, the power of the control command wave is constant, that is, the transmission power from the transmitter is constant.

[0003]

As described above, the transmission power from the ground control station in the conventional rocket launch control system, polar orbit satellite tracking control system, and the like is constant. Therefore, in a receiver of a wireless device mounted on a rocket or a satellite, it is necessary to widen the diminic range of a high-frequency signal processing system in consideration of cross-modulation at a strong electric field strength and high amplification at a weak electric field strength. In this case, there is a problem that the configuration and design of the receiver are difficult. Furthermore, this receiver captures unnecessary waves such as adjacent channels and harmonics (spurious) transmitted from the ground control station, and does not need to be transmitted together with a control command wave from the ground control station so that erroneous control is not performed. It is necessary to sufficiently suppress the wave level. In this case, there is a problem that the configuration of the transmission power output system is complicated. As described above, when the diminic range is narrow and the suppression of unnecessary waves is not sufficient, there is a problem that good line quality between the rocket and the satellite cannot be maintained.

SUMMARY OF THE INVENTION The present invention solves such problems in the prior art, and suppresses unnecessary waves in a diminic range of a high-frequency processing system in a receiver mounted on an air vehicle and transmission power from a ground control station. It is an object of the present invention to provide a transmission power control type control system which can be easily configured and maintain good channel quality without having to consider the above.

[0005]

In order to achieve the above object, the present invention provides a ground control system for transmitting at least a control command wave to an air vehicle and receiving a radio wave from the air vehicle to track the air vehicle. A transmission power control type control system provided in a station, wherein a distance and a distance change rate measurement for obtaining a distance and a distance change rate data between an air vehicle and a ground control station based on a round-trip time of radio waves during tracking of the air vehicle. Means, a flight position at which a control command wave transmitted from the ground control station reaches the flying object based on the distance and the distance change rate data, and a distance between the flight position and the ground control station, and the predicted distance Calculating means for calculating the radio wave propagation loss in the above, and attenuating the transmission power of the control command wave from the ground control station so that the received electric field strength at the flying object becomes substantially the same based on the calculation result of the radio wave propagation loss variable Configuration and a anti-attenuator entirety in
You.

[0006]

The transmission power control type control system of the present invention having such a configuration predicts the distance between the position of the air vehicle and the ground control station and calculates the radio wave propagation loss (free space loss) between them. The transmission power of the control command wave from the ground control station is controlled so that the received electric field strength at the flying object is substantially the same, so that the high-frequency processing system die of the receiver mounted on the flying object is controlled. It is not necessary to particularly consider the MINAC range and the suppression of unnecessary waves in the transmission power from the ground control station, so that the configuration is simplified and good line quality can be maintained.

[0007]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of a transmission power control type control system according to the present invention will be described below with reference to the drawings. FIG. 1 is a configuration example of a rocket launch control station system using a transmission power control type control system of the present invention. In FIG. 1, this example is:
A ground control station 10 in the rocket launch control system;
And a transmission power control device 12. The ground control station 10 transmits a control command wave following the flight elevation angle of the rocket R, and also outputs a data signal wave from the rocket R,
It has a parabolic antenna 22 that receives a reflected wave, and a receiver 24 that processes a signal received from the parabolic antenna 22 and outputs a data signal. Further, a distance / distance change rate measuring device 26 for measuring a distance and a distance change rate between the rocket R and the ground control station 10, a control command signal generating device 28 for outputting a control command signal, and a transmitter 30 Have.

[0008] The transmission power control device 12 is based on the distance and the rate of change of distance obtained by the distance / distance change rate measuring device 26, and includes an electronic computer 32 for performing arithmetic processing and instruction control described below; The transmission power from the computer 30
And a variable resistance attenuator 34 for changing the amount of attenuation by the instruction control from the control unit 2.

Next, the operation in this configuration will be described. First, the control command signal generator 28, the transmitter 30,
A radio wave Wa for distance / distance change rate measurement is transmitted through the variable resistance attenuator 34 and the parabolic antenna 22, and the parabolic antenna 22 receives a reflection wave from the rocket R or a response return wave Wb from a mounted transponder or the like. Further, the reception signal Sr from the receiver 24
It is input to the distance change rate measuring device 26. In the distance / distance change rate measuring device 26, the transmission start time of the transmission power from the transmitter 30 and the input time of the reception signal Sr, that is, the radio wave W
The distance L1 and the distance change rate ΔL1 between the rocket R and the ground control station 10 at time T1 are calculated based on the time required for reciprocation between “a” and the response return wave Wb and the known radio wave propagation distance (300,000 km) / sec. Is calculated and measured.

Next, the time T2 at which the control command wave Wc transmitted later reaches the rocket R is represented by T2 = T1 + (operating time of the transmission power control device 12) + (radio wave propagation time) (1) be able to. In the electronic computer 32, the expression (1)
Rocket R and Ground Control Station 10 at Time T2
L2 = L1 + ΔL1 (T2−T1) (2), and further, a free space loss which is a radio wave propagation loss of the control command wave Wc from the distance L2 and the transmission frequency obtained by the equation (2). Calculate Lo. The free space loss Lo increases when the transmission frequency is constant and the distance L2 increases. Based on the free space loss Lo, the computer 32 controls the variable resistance attenuator 34 so that the received electric field intensity at a receiver (not shown) mounted on the rocket R becomes a predetermined predetermined value.
The transmission power of the control command wave Wc from the parabolic antenna 22 is adjusted by instructing and controlling the amount of attenuation. That is, when the distance L2 between the rocket R and the ground control station 10 is small, the computer 32 instructs the attenuation of the variable resistance attenuator 34 to be large, controls the transmission, and transmits the control command wave Wc from the parabolic antenna 22. Reduce power.

When the distance L2 between the rocket R and the ground control station 10 is large, the computer 32 instructs the attenuation of the variable resistance attenuator 34 to be small, and controls the attenuation by controlling the control command wave from the parabolic antenna 22. A decrease in the transmission power of Wc is reduced. This process is similarly performed at many flight positions of the rocket R other than the distance L2. That is, the computer 32 instructs and controls the amount of attenuation of the variable resistance attenuator 34 so that the received electric field strength of the receiver mounted on the rocket R at each flight position always becomes a predetermined value. The transmission power of the control command wave Wc from the controller 22 is adjusted.

In this case, the received electric field intensity at the receiver mounted on the rocket R becomes a predetermined constant value, so that the dynamic range of the high-frequency signal processing system of the receiver mounted on the rocket R may be narrow. Become. As an example, when transmitting a control command wave from the ground control station 10 to the rocket R,
If the distance during this period changes from 500 m to 1000 km, the dynamic range of the rocket receiver can be reduced to 33 dB. Further, the allowable level of the unnecessary wave radiated from the transmitter 30 together with the control command wave may be higher. When the control command wave is transmitted from the ground control station 10 to the rocket R, if the dynamic range of the receiver of the rocket R is, for example, 70 dB, the receiver may capture unnecessary waves to prevent erroneous control. To do so, the level of the unnecessary wave transmitted from the transmitter 30 needs to be reduced to 70 dB or more with respect to the fundamental wave of the control command wave. When the distance between the rocket R and the ground control station 10 changes from 500 m to 1000 km, the dynamic range is reduced by 33 dB, so that the allowable value of the unnecessary wave level becomes 37 dB or more with respect to the fundamental wave of the control command wave.

In this embodiment, the control command power from the transmitter 30 is attenuated by the variable resistance attenuator 34 by instruction control, but the transmission system in the transmitter 30 is controlled to reduce the control command power. May be adjusted.

[0014]

As described above, the transmission power control type control system of the present invention predicts the distance between the position of the flying object and the ground control station, and the radio wave propagation loss (free space loss) during this period.
The transmission power from the ground control station is controlled so that the received electric field strength at the flying vehicle is substantially the same based on the calculation results of the above, so the high frequency processing system of the receiver mounted on the flying vehicle There is no need to particularly consider the nack range and the suppression of unnecessary waves in the transmission power from the ground control station, which has the effect of simplifying the configuration and maintaining good line quality.

[Brief description of the drawings]

FIG. 1 is a configuration diagram of a rocket launch control station system to which an embodiment of a transmission power control type control system of the present invention is applied.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 10 Ground control station 12 Transmission power control device 22 Parabolic antenna 24 Receiver 26 Distance / distance change rate measuring device 28 Control command signal generator 30 Transmitter 32 Computer 34 Variable resistance attenuator R Rocket

──────────────────────────────────────────────────続 き Continued on the front page (58) Field surveyed (Int. Cl. ⁶ , DB name) G01S 7/00-7/42 G01S 13/00-13/95 H04B 1/60 H04B 3/46-3 / 48 H04B 17/00-17/02 H04B 7/24-7/26 113 H04Q 7/00-7/38

Claims (1)

(57) [Claims] 1. A transmission power control type control system provided in a ground control station for transmitting at least a control command wave to a flying object and receiving a radio wave from the flying object to track the flying object, wherein the flight Distance / distance change rate measurement means for obtaining distance and distance change rate data between the flying object and the ground control station based on the round trip time of the radio wave during body tracking; andthe ground and distance change rate data based on the distance and distance change rate data A flight position at which the control command wave transmitted from the control station reaches the flying object, a distance between the flight position and the ground control station, and a calculating unit that calculates a radio wave propagation loss at the predicted distance; Variable resistance attenuator for attenuating the transmission power of a control command wave from a ground control station so that the received electric field strength at the flying object is substantially the same based on the calculation result of the radio wave propagation loss
And a transmission power control type traffic control system.