Engine assembly of a rocket engine

Abstract

Engine assembly (100) of a rocket engine, comprising: an afterburning chamber (1) with a gas inlet opening (27) for gas to flow into the afterburning chamber (1) and a gas outlet opening (20) for gas to flow out; a gas-fillable compensation chamber (3); a control chamber (2) that can be filled with gas; and a nozzle needle (4) which is arranged to be axially displaceable such that a first end region (28) of the nozzle needle (4) can be inserted at least partially into the gas outlet opening (20); wherein the nozzle needle (4) has a piston assembly (5) at a second end region, wherein a first section (29) of the piston assembly (5) is arranged in the compensation chamber (3) and a second section (7) of the piston assembly (5) is arranged in the control chamber (2) and can be pressurized by filling the control chamber (2) with gas such that the nozzle needle (4) experiences an axial force in the direction of the gas outlet opening (20); wherein the afterburner chamber (1) is separated from the control chamber (2) by a bulkhead (10); and wherein the piston assembly (5) is displaceable in an intermediate chamber (30), wherein the intermediate chamber (30) is sealed against the compensation chamber (3) and is fluidically connected to an ambient air.

Description

[0001] The present invention relates to an engine device of a rocket engine.

[0002] For missile defense, interceptor missiles are brought into collision with the ballistic targets to be destroyed, with the kinetic energy converted during the collision destroying the target. However, the targets themselves move at high speeds and on trajectories that are only partially predictable, making highly agile control of the interceptor missiles essential.

[0003] Reactive thrust and attitude control systems are typically used for this purpose. These systems can be operated by discrete thrust pulses, switching the engines on and off. In this case, thrust is used solely for course correction. Continuous thrust controls are also available, allowing for precise thrust adjustment.

[0004] One way to regulate thrust is to insert or remove a nozzle needle, that is, an elongated body, into or out of a nozzle opening. This reduces the effective cross-section of the nozzle, that is, the portion of the cross-section available to the outgoing gas, and thereby alters the thrust. Such an engine device is known from US Patent 6,986,246 B2, in which the nozzle needle is mechanically displaced in the axial direction. Further prior art is disclosed in US Patent 6,227,247 B1.

[0005] One of the aims of the invention is to enable improved thrust adjustment.

[0006] This problem is solved by a propulsion device with the features of claim 1. Advantageous embodiments of the invention are the subject of the dependent claims.

[0007] The invention relates to an engine assembly of a rocket engine, comprising an afterburner chamber with a gas inlet opening for gas flowing into the afterburner chamber and a gas outlet opening or nozzle designed for gas flowing out of the afterburner chamber. The engine assembly further comprises a gas-fillable compensation chamber and a gas-fillable control chamber. A nozzle needle is arranged in an axially displaceable manner such that a first end region of the nozzle needle can be at least partially inserted into the gas outlet opening. A second end region of the nozzle needle has a piston assembly, wherein a first section of the piston assembly is arranged in the compensation chamber and can be pressurized by a gas located in the compensation chamber such that the nozzle needle experiences an axial force in the direction of the gas outlet opening.A second section of the piston assembly is arranged in the control chamber and can be pressurized by filling the control chamber with gas in such a way that the nozzle needle experiences an axial force in the direction away from the gas outlet opening.

[0008] Depending on the gas pressure conditions in the three chambers—the equalization chamber, the control chamber, and the afterburner chamber—corresponding axial forces are exerted on the nozzle needle. By adjusting the pressures, the position of the nozzle needle can therefore be precisely set. The pneumatic control achieves a very short response time, allowing the effective cross-section of the afterburner's gas outlet to be varied extremely quickly. This enables precise adjustment of the thrust of the engine.

[0009] According to a preferred embodiment, the engine device has a control unit configured to adjust the axial position of the nozzle needle by changing the gas pressure of a gas located in the control chamber. Changing the gas pressure alters the axial force on the nozzle needle, thus allowing the position of the nozzle needle and, consequently, the effective cross-section of the gas outlet opening to be precisely adjusted.

[0010] According to a preferred embodiment of the engine device, the control unit is further configured to adjust the gas pressure of a gas in the compensation chamber. This allows adjustment of both the axial force on the nozzle needle towards the gas outlet opening and away from the gas outlet opening.

[0011] According to a preferred embodiment, the engine device includes a sensor configured to measure the axial position of the nozzle needle. Based on the measured position, the control unit can, for example, adjust the gas pressure in the control chamber and / or compensation chamber such that the nozzle needle is moved to a predetermined axial position.

[0012] According to a preferred embodiment of the engine device, the afterburner chamber is fluidically connected to the equalization chamber. Thus, the pressure in the afterburner chamber essentially corresponds to the pressure in the equalization chamber, apart from dynamic fluctuations due to the displacement of the nozzle needle and flow losses caused by gas overflow. Preferably, the afterburner chamber is designed such that, when the control chamber is vented (i.e., not pressurized with gas), the axial force on the nozzle needle in the direction of the gas outlet is greater than the axial force exerted on the nozzle needle away from the gas outlet due to the gas flow in the afterburner chamber. The control chamber serves to generate a counterforce that displaces the nozzle needle away from the gas outlet.Since only the pressure difference is required, the nozzle needle is axially displaced by applying even a small amount of gas pressure, so that a slight change in gas pressure is sufficient to set the exact axial position of the nozzle needle. This keeps the adjustment time very short.

[0013] According to a preferred embodiment of the engine device, the control chamber is arranged axially between the compensation chamber and the afterburner chamber. The axial direction corresponds to the axial displacement direction of the nozzle needle.

[0014] According to the invention, the afterburner chamber and the control chamber are separated by a bulkhead.

[0015] According to a further development of the engine device, the compensation chamber and / or the afterburner chamber are arranged symmetrically around an axial displacement axis of the nozzle needle.

[0016] According to a further development of the engine device, the gas outlet opening can be completely closed by inserting the nozzle needle. The thrust provided by the engine device can thus be continuously varied between zero and a maximum predetermined value, with the maximum value corresponding to a position in which the nozzle needle is completely displaced from the gas outlet opening.

[0017] According to the invention, the piston assembly is displaceable in an intermediate chamber, wherein the intermediate chamber is sealed against the compensation chamber and fluidically connected to ambient air.

[0018] The invention will now be explained with reference to the figures in the drawings. The figures show: Fig. 1 a schematic side view of a propulsion device according to an embodiment of the invention; Fig. 2 a schematic rear view of the in Fig. 1 engine device shown; Fig. 3 A schematic cross-sectional view of the engine device, which is shown in a section along the in Fig. 1 shows axis AA; Fig. 4 A schematic cross-sectional view of the engine device, which is shown in a section along the in Fig. The axis BB shown in point 2 yields; and Fig. 5 A schematic cross-sectional view of the engine device, which is shown in a section along the in Fig. The CC axis shown in section 2 is obtained.

[0019] Where appropriate, the described embodiments and further developments can be combined with one another as desired. Further possible embodiments, further developments, and implementations of the invention also include combinations of features of the invention described previously or subsequently with regard to the exemplary embodiments, even if not explicitly mentioned.

[0020] The accompanying drawings are intended to provide a further understanding of the embodiments of the invention. They illustrate embodiments and, in conjunction with the description, serve to explain the principles and concepts of the invention. Other embodiments and many of the aforementioned advantages become apparent with reference to the drawings. The elements of the drawings are not necessarily shown to scale relative to one another. Identical reference numerals denote identical or similarly functioning components.

[0021] In Fig. Figure 1 shows a schematic side view of a propulsion device 100, which has a housing with a front housing section 11 and a rear housing section 12.

[0022] Fig. 2 shows a rear view of the in Fig. Engine device shown in 1.

[0023] In Fig. Figure 3 is a cross-sectional view of the engine device 100 along the in Fig. 1. Axis AA is illustrated.

[0024] Fig. Figure 4 shows the engine device in a schematic cross-sectional view along axis BB. Fig. 2 and Fig. 5 along the CC axis of the Fig. 2.

[0025] The engine device 100 has an afterburner chamber 1, which is connected via gas inlet openings 27 to a gas reservoir or a gas generator. The gas reservoir or gas generator introduces gas into the afterburner chamber 1, which is accelerated through a gas outlet opening or engine nozzle 20 and discharged from the afterburner chamber 1. The discharged gas generates thrust, which can be used to change the flight direction of a missile equipped with the engine device.

[0026] The thrust is varied by changing the effective cross-section of the gas outlet opening 20. For this purpose, a nozzle needle 4 is axially displaceable within the engine device 100, with a first end section 28 of the nozzle needle 4 being at least partially insertable into the gas outlet opening 20, thus allowing the effective cross-section of the gas outlet opening 20 to be varied. The nozzle needle has a cylindrical section that tapers in the first end section 28. Preferably, the end section 28 is pointed. However, according to further embodiments, the end section can also be rounded or cylindrical. The gas outlet opening 20 can preferably be completely closed by inserting the nozzle needle 4.

[0027] The afterburner chamber 1 is separated from a control chamber 2 by a bulkhead 10. Seals 25, 26 are arranged between the bulkhead 10 and the housing. A seal retaining plate 15 is screwed to the bulkhead 10 by means of seal retaining screws 16, with a nozzle needle seal 13 being attached to the seal retaining plate 15. The nozzle needle 4 is inserted into the afterburner chamber 1 through the nozzle needle seal 13 and the seal retaining plate 15 and is axially displaceable, with the afterburner chamber 1 being sealed by the nozzle needle seal 13.

[0028] The engine device 100 further comprises a compensating chamber 3, wherein the control chamber 2 is arranged axially between the afterburning chamber 1 and the compensating chamber 3. An intermediate chamber 30 is arranged between the compensating chamber 3 and the control chamber 2. Preferably, the compensating chamber 3 and / or the afterburning chamber 1 are arranged symmetrically around an axial displacement axis of the nozzle needle 4.

[0029] The nozzle needle 4 has a piston assembly 5 at a second end region, which is axially opposite to the first end region 28. The piston assembly 5 comprises a first section 29, which is axially displaceable and positively locked within the compensation chamber 3. The piston assembly 5 further comprises a second section 7, which is axially displaceable and positively locked within the control chamber 2. The first section 29 is connected to the second section 7 of the piston assembly 5 via a piston screw 8. A third section 6 faces away from the afterburner chamber 1 and is axially displaceable and positively locked within the intermediate chamber 30. Piston seals 9 are enclosed in a radially outer direction between the second section 7 and the third section 6 of the piston assembly 5, preventing fluidic contact between the control chamber 2 and the intermediate chamber 30.Further seals 14 are arranged between the rear housing section 12 and a cylindrical protrusion of the third section 6 of the piston assembly 5, so that the cylindrical protrusion is axially displaceable in the compensation chamber 3 and at the same time the compensation chamber 3 is sealed against the intermediate chamber 30.

[0030] The intermediate chamber 30 is fluidically connected to ambient air via vent openings 21, so that a neutral ambient pressure prevails in the intermediate chamber 30 and the nozzle needle 4 can be displaced axially in the intermediate chamber 30 without any air in the intermediate chamber 30 exerting an axial force on the nozzle needle 4.

[0031] Preferably, the afterburner chamber 1 is fluidically connected to the compensation chamber 3. Thus, the compensation chamber 3 and the afterburner chamber 1 can be connected to the same gas reservoir or gas generator, or the afterburner chamber 1 and the compensation chamber 3 can be connected to each other via a fluid line or gas line.

[0032] The piston assembly 5 has a sensor port 17, which can be connected to, or is connected to, a sensor assembly, which can also be part of the engine assembly 100. The sensor assembly can be screwed to and attached to a screw hole 23 of the rear housing section 12. The sensor assembly is designed to measure the axial position of the nozzle needle 4.

[0033] The afterburner chamber 1 also has a connection 18, which can be connected to, or is connected to, a pressure / temperature transducer, which may also be part of the engine assembly 100. The pressure / temperature transducer is designed to measure a pressure or temperature in the afterburner chamber 1. Furthermore, the control chamber 2 has a connection 19, which can be connected to, or is connected to, a pressure / temperature transducer. This pressure / temperature transducer may be identical to or different from the pressure / temperature transducer connected to the connection 18 of the afterburner chamber 1. The pressure / temperature transducer is designed to measure a pressure or temperature in the control chamber 2 and may also be part of the engine assembly 100.

[0034] A gas located in the compensation chamber 3 pressurizes the first section 29 of the piston assembly 5 such that the nozzle needle 4 forms a Fig.5. Axial balancing force F shown A in the direction of the gas outlet opening 20 of the afterburner chamber 1. Due to the airflow through the gas outlet opening 20 of the afterburner chamber 1, the first end region 28 of the nozzle needle 4 is also pressurized, so that an air force F L The balancing force F is exerted from the gas outlet opening 20 onto the jet needle 4. The balancing chamber is preferably dimensioned, that is, a size and / or geometric shape of the balancing chamber is chosen such that the balancing force F A with the jet needle fully retracted, that is, in a position in which the jet needle 4 is moved as far as possible out of the gas outlet opening 20 of the afterburner chamber 1, greater than the air force F L This results in an effective force acting in the direction of the gas outlet opening 20.

[0035] The control chamber 2 has a gas opening 24 through which gas can be introduced into or extracted from the control chamber 2. By introducing gas into the control chamber 2 via the gas opening 24, a steering force F can be generated. S The pressure is generated on the jet needle 4, which is created by the gas pressure of the gas in the control chamber 2 and points away from the gas outlet opening 20. The gas flow into and out of the control chamber 2 can be controlled by two 2 / 2-way valves or one 3 / 3-way valve.

[0036] The propulsion device 100 preferably further comprises a control unit (not shown) configured to adjust the axial position of the nozzle needle 4 by changing the gas pressure of a gas located in the control chamber 2. Preferably, the control unit is connected to the sensor unit and receives a current axial position of the nozzle needle 4 from the sensor unit. Based on the current axial position of the nozzle needle 4, the control unit increases or decreases the gas pressure of the gas located in the control chamber 2 until the current axial position measured by the sensor unit corresponds to a predetermined position. By increasing the gas pressure of the gas located in the control chamber 2, the control force F is increased. SThe pressure of the gas jet, which points away from the gas outlet opening 20, is increased so that by increasing the gas pressure, the jet needle 4 can be moved further out of the gas outlet opening 20. Conversely, by decreasing the gas pressure of the gas in the control chamber 2, the control device can increase the control force F. S decrease, so that the jet needle 4 is affected by the balancing force F A The nozzle needle is moved or inserted further into the gas outlet opening 20. This reduces the effective cross-section of the gas outlet opening 20. The control device is therefore designed to continuously change the axial position of the nozzle needle 4.

[0037] The invention is not limited to the embodiments shown. According to further embodiments, the control device can also be configured to adjust the pressure of a gas in the compensation chamber 3. Preferably, the control device can adjust both the gas pressure in the compensation chamber and the gas pressure in the control chamber 2. The arrangement of the compensation chamber 3, control chamber 2, and afterburner chamber 1 is also not limited to the embodiments shown. According to further embodiments, the compensation chamber 3 can be arranged between the control chamber 2 and the afterburner chamber 1. REFERENCE MARK LIST 1 Afterburner chamber 2 Tax Chamber 3 Compensation chamber 4 jet needle 5 Piston assembly 6 third section of the piston assembly 7 second section of the piston assembly 8 Piston screw 9 Piston seal 10 Schott 11 front housing section 12 rear housing section 13 Nozzle needle seal 14 Seal 15 Sealing retaining plate 16 Seal retaining screw 17 Sensor connection 18 Afterburner chamber connection to pressure / temperature transducer 19 Control chamber connection to pressure / temperature transducer 20 Gas outlet opening 21 ventilation openings 22 housing screws 23 screw holes 24 Gas opening 25 Seal 26 Seal 27 gas inlet openings 28 first end area of ​​the jet needle 29 first section of the piston assembly 30 Intermediate chamber 100 engine device

Claims

Engine device (100) of a rocket engine, comprising: an afterburning chamber (1) with a gas inlet opening (27) for gas flowing into the afterburning chamber (1) and a gas outlet opening (20) for gas flowing out; a gas-fillable compensation chamber (3); a gas-fillable control chamber (2); and a nozzle needle (4), which is arranged to be axially displaceable such that a first end region (28) of the nozzle needle (4) can be inserted at least partially into the gas outlet opening (20);wherein the nozzle needle (4) has a piston assembly (5) at a second end region, wherein a first section (29) of the piston assembly (5) is arranged in the compensation chamber (3) and can be pressurized by a gas located in the compensation chamber (3) such that the nozzle needle (4) experiences an axial force in the direction of the gas outlet opening (20), and wherein a second section (7) of the piston assembly (5) is arranged in the control chamber (2) and can be pressurized by filling the control chamber (2) with a gas such that the nozzle needle (4) experiences an axial force in the direction away from the gas outlet opening (20); wherein the afterburner chamber (1) is separated from the control chamber (2) by a bulkhead (10); and wherein the piston assembly (5) is displaceable in an intermediate chamber (30), the intermediate chamber (30) being sealed against the compensation chamber (3) and fluidically connected to an ambient air. Engine device (100) according to claim 1, comprising a control device which is configured to adjust an axial position of the nozzle needle (4) by changing the gas pressure of a gas located in the control chamber (2). Engine device (100) according to claim 2, wherein the control device is further configured to adjust a gas pressure of a gas in the compensation chamber (3). Engine device (100) according to one of the preceding claims, with a sensor device which is configured to measure an axial position of the nozzle needle (4). Engine device (100) according to one of the preceding claims, wherein the afterburning chamber (1) is fluidically connected to the compensation chamber (3). Engine device (100) according to one of the preceding claims, wherein the control chamber (2) is arranged in the axial direction between the compensation chamber (3) and the afterburning chamber (1). Engine device (100) according to one of the preceding claims, wherein the compensation chamber (3) and / or the afterburning chamber (1) are arranged symmetrically around an axial displacement axis of the nozzle needle. Engine device (100) according to one of the preceding claims, wherein the gas outlet opening (20) can be completely closed by inserting the nozzle needle (4).

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