JPH079212B2 - Integral rocket ramjet engine - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION [Industrial field of application] The present invention relates to an integral unit used as a propulsion device for a supersonic vehicle that can fly only once, such as a missile.
For rocket and ramjet engines.

[Conventional technology]

The configuration of a conventional integral rocket ramjet engine will be described with reference to FIG.

The rear half of the supersonic spacecraft 1 is the propulsion unit. As a main constituent element of the propulsion unit, a fuel tank 2 is provided in the front part and a combustor 3 is provided in the rear part coaxially. An air intake duct 4 is provided outside the combustor 3 to direct the population forward and to place the outlet on the front side of the combustor 3. The number of air intake ducts 4 is usually 1 to 4. Further, the outlet of the air intake duct 4 is closed by a partition plate 5 along the wall of the combustor 3. The combustor 3 is initially packed with a solid type booster propulsion unit 6, and a booster ignition device 7 is provided at the rear end thereof. At the rear end of the combustor 3, there is provided a booster nozzle 8 with its injection port facing rearward. A fuel pump 9 and a fuel control valve 10 are provided between the fuel tank 2 and the combustor 3, and a pipe is provided at the rear of each air intake duct 4 from the fuel tank 2 through the fuel pump 9 and the fuel control valve 10 by piping. It is connected to the fuel nozzle 11.

Further, a ramjet ignition device (explosive charge type igniter) 12 is provided on the rear side of the air intake duct 4.

In the above configuration, the flying vehicle 1 starts its operation when it is dropped from a flying aircraft or is launched by an auxiliary rocket.

First, the booster propellant 6 starts to burn by the booster ignition device 7 and operates as a solid rocket for a while. The high-temperature high-pressure gas generated by the combustion of the booster propellant 6 is discharged at a high speed rearward through the booster nozzle 8 to generate thrust. This stage is called the booster phase, and accelerates the flying vehicle 1 to supersonic speed (more precisely, above the self-sustaining speed of the ramjet).

When the booster propellant 6 is burned out, the partition plate 5 and the booster nozzle 8 are separated, and air comes into the combustor 3 from the air intake duct 4. Therefore, the fuel pump 9 sucks the liquid fuel from the fuel tank 2, sends it to the fuel nozzle 11 through the fuel control valve 10, sprays it into the air flow, and ignites it by the ramjet ignition device 12, and thereafter it operates as a ramjet engine. To do. Booster propellant 6
The phase from the burnout to the ignition is called the transient phase, and the phase after the ignition is called the ramjet phase.

When moving to the ramjet phase, a part of the flame circulates in the combustor 3 and can continue to burn due to the circulation flow of the flame becoming a fire seed. It only needs to be actuated once at the beginning of the, and usually a pyrotechnic igniter (cartridge igniter) is used.

The operation duration of the explosive igniter 12 is about several seconds to 10 seconds.

[Problems to be Solved by the Invention]

As explained above, when a pyrotechnic igniter is used in the ramjet igniter, it operates only once at the beginning of the ramjet phase.

There is no problem with normal flight, but after the operation of the explosive ignition igniter for starting is completed, the flying body violently moves (turns) and the inflow condition of air changes and the circulating flow in the combustor 3 changes. If it disappears even for a moment, there is a risk of loss of thrust due to flame "blown out" (misfire).

It can be operated many times during flight by using an electric spark type ignition device like a gasoline engine, but because the ignition energy is small and it is difficult to install it on an integral rocket ramjet engine Not normally used.

[Means for Solving the Problems]

 The present invention takes the following means in order to solve the above problems.

In other words, as an integral rocket / ramjet engine, a flight control device that controls the steering wings, etc.,
In an integral rocket ramjet engine for a flying vehicle equipped with a ramjet phase starting explosive igniter, a predetermined number of explosive prevention igniters for receiving a signal from the above flight control device, An integral rocket ramjet engine characterized in that the flight control device ignites the predetermined number of explosive-type igniters sequentially in a predetermined time series when the flying body performs a predetermined vigorous motion.

[Action]

By the above means, from the flight control device of the flying body,
A signal for operating the explosive igniter is sequentially output in a predetermined time series from a predetermined time before the flying body starts a predetermined vigorous motion. That is, it is set in advance so that the explosive-type igniter continuously operates while the flying body continues the predetermined vigorous motion.

If the predetermined vigorous exercise is to be performed a plurality of times, the explosive-type igniters are separately operated to operate in a predetermined time series.

In this way, since the explosive igniter continues to operate even during intense exercise, misfire (blown out flame) does not occur,
You will surely be able to continue to promote toward your goals.

〔Example〕

An embodiment of the present invention will be described with reference to FIGS.

FIG. 1 is an overall view, FIG. 2 is a block diagram, FIG. 3 is a calculation flow chart, and FIG. 4 is an operation explanatory view.

The parts described in the conventional example will be omitted to avoid redundancy, and the parts relating to the present invention will be mainly described.

There are two air intake ducts 4 on the flying body 1 shown in FIG.
There are two, and each duct has two No. 1 explosive-type igniters 12
a, No. 2 explosive igniter 12b and No. 3 explosive igniter 12c, No.
4 Attach the gunpowder type igniter 12d. Therefore, there are a total of four explosive igniters.

Further, there is a flying body control device (not shown), and the steering blade 20 at the rear end is controlled via a servo motor (not shown). The output of the flying vehicle control device is connected to each explosive igniter.

In the above configuration, the first
The explosive igniter 12a is activated at the start of the ramjet phase. 3 is left, so 3 for "vigorous exercise"
It is possible up to times. As a general rule, the duration of each "vigorous exercise" is shorter than the duration of operation of one explosive-type igniter. If the "vigorous exercise" is performed for longer than the operation duration of one explosive type igniter, a plurality of explosive type igniters are continuously operated. Instead, the number of times "vigorous exercise" is allowed is reduced.

The flying body 1 flies in a straight line most of the time, and the number of times of "vigorous exercise" is required is once to several times per flight. Therefore, the purpose can be sufficiently achieved by providing several explosive-type igniters.

The detailed operation will be described below.

As shown in FIG. 3, the flight control device is composed of a target sensing unit, a posture sensing unit, and a computing unit.
The required turning angle and turning intermittent time are obtained from the self-confidence posture, and a signal is sent to the servo motor driving the steering blade 20 and the explosive type igniter.

FIG. 4 is a flow chart showing the operation sequence of the system shown in FIG. This operating sequence is executed after each turn.

FIG. 5 shows the time relationship between the operation of the explosive igniter and the motion of the flying object. That in flight control device, than continuing time series t ₂ ~t ₃ and the turning angle exceeding the misfire limit l ₀ pyrotechnic igniter previously determined, the No.2 pyrotechnic igniter 12b to t ₁ before the predetermined time Ignite by sending an ignition signal. If the operation duration time t _{1 to} t ₄ of the No. 2 explosive type igniter 12b is longer than the time t _{2 to} t ₃ exceeding the misfire limit l ₀ , one No. 2 explosive type igniter 12b is activated to finish. .

After that, when the flying body 1 makes a larger and longer turn, the No. 3 explosive type igniter 12c is similarly set to the misfire limit time t ₆
Ignited earlier predetermined time t _5, if further duration t ₆ ~t ₇ of the misfire limit time determined is longer than the operating duration of No.3 pyrotechnic igniter 12c t ₆ ~t _8, Its operation end time
the time t ₇ prior to t ₈ to ignite the No.4 pyrotechnic igniter 12d. N
o.3 The time t _{6 to} t ₁₀ during which the explosive igniter 12c and the No. 4 explosive igniter 12d are continuously operating is the misfire limit duration t _{6 to} t _7.
Is fully covered.

As described above, when the flying vehicle 1 is aiming at the target while performing a violent motion exceeding the misfire limit l ₀ , the integral rocket ramjet engine always operates the explosive igniter to reliably operate the ramjet. Let's fly 1
Will be able to reach the goal.

As described in the above embodiments, the present invention does not activate the explosive-type igniter after a misfire, but when a misfire is predicted due to vigorous exercise, it is necessary (before the misfire occurs). The feature is that the operation of the explosive igniter is started and continued during intense exercise.

〔The invention's effect〕

As described above, the present invention has the following effects.

The integral rocket ramjet engine that uses liquid fuel has the excellent features that the thrust force per fuel weight flow rate is large and the thrust control is easy. However, there was a risk of causing a misfire (blown out) when performing a vigorous exercise, but the integral rocket ramjet engine of the present invention can prevent a misfire, enable a vigorous exercise, and fly. It has a long flight distance and provides a supersonic flying object that is easy to control.

[Brief description of drawings]

FIG. 1 is a block diagram of an embodiment of the present invention, FIG. 2 is a block diagram of FIG. 1, FIG. 3 is a flow chart of the same embodiment, and FIG. 4 is an operation explanatory view of the same embodiment. FIG. 5 is a block diagram of a conventional example. 1 ... Flying object, 2 ... Fuel tank, 3 ... Combustor,
4 ... Air intake duct, 5 ... Partition plate, 6 ... Booster propellant, 7 ... Booster ignition device, 8 ... Booster nozzle, 9 ... Fuel pump, 10 ... Fuel control valve, 11 ... … Fuel nozzle, 12… Ramjet igniter, 12a… No.1
Explosive-type igniter, 12b ... No.2 Explosive-type igniter, 12c ... No.3
Explosive type igniter, 12d …… No.4 Explosive type igniter, 20 …… Steering blade.

Claims (1)

[Claims] 1. A flight control device for controlling steering wings and the like,
An integral rocket ramjet engine for a flying vehicle equipped with a ramjet phase starting explosive igniter and a predetermined number of misfire preventing explosive igniters receiving a signal from the above flight control device. The integral rocket ramjet engine, wherein the flight control device sequentially ignites the predetermined number of explosive-type igniters in a predetermined time series when the flying body performs a predetermined violent motion.