Orthogonal Acceleration Coaxial Cylinder Time of Flight Mass Analyser

Abstract

A Time of Flight mass analyser is disclosed comprising an annular ion guide having a longitudinal axis and comprising a first annular ion guide section and a second annular ion guide section. Ions are introduced into the first annular ion guide section so that the ions form substantially stable circular orbits within the first annular ion guide section about the longitudinal axis. An ion detector is disposed within the annular ion guide. Ions are orthogonally accelerated in a first axial direction from the first annular ion guide section into the second annular ion guide section. An axial DC potential is maintained along at least a portion of the second annular ion guide section so that the ions are reflected in a second axial direction which is substantially opposed to the first axial direction. The ions undergo multiple axial passes through the second annular ion guide section before being detected by the ion detector.

Claims

1. A Time of Flight mass analyser comprising: an annular ion guide having a longitudinal axis; a first device arranged and adapted to introduce ions into said annular ion guide, wherein an electric field is applied to the annular ion guide so that said ions form substantially stable circular orbits within said annular ion guide about said longitudinal axis; an ion detector disposed within said annular ion guide; a second device arranged and adapted to orthogonally accelerate ions in a first axial direction from said substantially stable circular orbits within said annular ion guide such that ions follow substantially spiral paths as they pass through said annular ion guide; and a third device arranged and adapted to maintain an axial DC potential along at least a portion of said annular ion guide so that said ions are reflected in a second axial direction which is substantially opposed to said first axial direction and so that said ions undergo multiple axial passes through said annular ion guide before being detected by said ion detector.

2. (canceled)

3. A Time of Flight mass analyser as claimed in claim 1, wherein an ion detecting surface of said ion detector is positioned substantially at an isochronous plane which is substantially perpendicular to said longitudinal axis.

4. A Time of Flight mass analyser as claimed in claim 1 wherein said second device is arranged and adapted to apply a pulsed axial electric field.

5. A Time of Flight mass analyser as claimed in claim 4, wherein said second device is further arranged and adapted to apply a pulsed radial electric field at substantially the same time as said pulsed axial electric field.

6. A Time of Flight mass analyser as claimed in claim 5, wherein said second device is arranged and adapted to apply a pulsed radial electric field at substantially the same time as said pulsed axial electric field so that said ions assume non-circular or elliptical orbits in a plane perpendicular to said longitudinal axis.

7. (canceled)

8. A Time of Flight mass analyser as claimed in claim 1, wherein said second device is arranged and adapted to orthogonally accelerate said ions so that time of flight dispersion occurs only in a longitudinal direction.

9. (canceled)

10. A Time of Flight mass analyser as claimed in claim 1, wherein said ion detector has an annular, part annular or segmented annular ion detecting surface.

11. (canceled)

12. A Time of Flight mass analyser as claimed in claim 1, wherein said annular ion guide comprises an inner cylindrical electrode arrangement.

13. A Time of Flight mass analyser as claimed in claim 10, wherein said inner cylindrical electrode arrangement is axially segmented and comprises a plurality of first electrodes.

14. A Time of Flight mass analyser as claimed in claim 12, wherein said annular ion guide comprises an outer cylindrical electrode arrangement.

15. A Time of Flight mass analyser as claimed in claim 14, wherein said outer cylindrical electrode arrangement is axially segmented and comprises a plurality of second electrodes.

16. A Time of Flight mass analyser as claimed in claim 14, wherein an annular time of flight ion guiding region is formed between said inner cylindrical electrode arrangement and said outer cylindrical electrode arrangement.

17-20. (canceled)

21. A Time of Flight mass analyser as claimed in claim 1, wherein said spiral paths are non-helical along at least a portion of said annular ion guide such that the ratio of curvature to torsion of said spiral paths varies or is non-constant.

22. A Time of Flight mass analyser as claimed in claim 1, further comprising a device arranged and adapted to maintain one or more half-parabolic or other DC potentials along a portion of said annular ion guide in order to reflect ions.

23. A Time of Flight mass analyser as claimed in claim 1, further comprising a device arranged and adapted to maintain one or more parabolic DC potentials along a portion of said annular ion guide so that ions undergo simple harmonic motion.

24-26. (canceled)

27. A Time of Flight mass analyser as claimed in claim 1, wherein electrodes in said annular ion guide are segmented so that at least a first electric field sector and a second electric field sector are formed in use.

28. A Time of Flight mass analyser as claimed in claim 27, further comprising a control system arranged and adapted at a first time T1 to inject ions substantially tangentially into said first electric field sector whilst maintaining a substantially zero radial electric field in said first electric field sector so that said ions experience a substantially field free region whilst being injected into said annular ion guide.

29. A Time of Flight mass analyser as claimed in claim 28, wherein said control system is further arranged and adapted to maintain a radial electric field in said second electric field sector so that at a second later time T2 ions pass from said first electric field sector into said second electric field sector and become radially confined.

30. A Time of Flight mass analyser as claimed in claim 29, wherein said control system is further arranged and adapted at a third time T3, wherein T3>T1, to cause a radial electric field to be maintained in said first electric field sector so that as ions pass from said second electric field sector into said first electric field sector said ions continue to be radially confined and form substantially stable circular orbits within said annular ion guide.

31-32. (canceled)

33. A Time of Flight mass analyser as claimed in claim 1, wherein said ion detector is arranged and adapted to detect ions impacting or impinging upon an ion detection surface of said ion detector.

34-40. (canceled)

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0171] Various embodiments of the present invention will now be described, by way of example only, and with reference to the accompanying drawings in which:

[0172] FIG. 1 shows the principle of spatial focusing;

[0173] FIG. 2 shows ion velocity and phase space ellipses;

[0174] FIG. 3 illustrates Liouville's theorem;

[0175] FIG. 4 shows a W-shaped Time of Flight region in a conventional Time of Flight mass analyser;

[0176] FIG. 5 shows an end view of a preferred Time of Flight mass analyser;

[0177] FIG. 6A shows ions confined in a stable orbit and FIG. 6B shows a pulsed voltage being applied to a grid which is placed inside the analyser between the two cylinders;

[0178] FIG. 7A shows an embodiment and FIG. 7B shows another embodiment of the present invention;

[0179] FIG. 8A shows an embodiment wherein ions are initially confined, FIG. 8B shows a parabolic potential being applied to one side of the ion path, FIG. 8C shows ions oscillating along a parabolic potential and FIG. 8D shows the ions being transmitted to an ion detector;

[0180] FIG. 9A shows ions being confined initially, FIG. 9B shows ions being orthogonally accelerated, FIG. 9C shows ions being detected by an ion detector located at the exit of a field free region, FIG. 9D shows an embodiment wherein ions experience a parabolic potential, FIG. 9E shows an embodiment wherein ions oscillate within a parabolic potential and FIG. 9F shows an embodiment wherein ions are transmitted to an ion detector located at the exit of a field free region;

[0181] FIG. 10 shows evolution of phase space in pre push state with beam stop;

[0182] FIG. 11 shows a further embodiment of the present invention comprising a gridless geometry with pulsed voltages shown as dotted lines;

[0183] FIG. 12 shows a schematic of the geometry of a Time of Flight mass analyser which was modelled;

[0184] FIG. 13 shows a view of the co-axial geometry of a Time of Flight mass analyser which was modelled;

[0185] FIG. 14 shows a comparison of ion peaks due to an analytic system and a Time of Flight mass analyser according to an embodiment of the present invention;

[0186] FIG. 15 shows a comparison of time of flight peaks due to an analytic system and a Time of Flight mass analyser according to an embodiment of the present invention;

[0187] FIG. 16A shows a preferred embodiment of the present invention in cross-section and shows an ion beam initially undergoing stable circular orbits prior to being orthogonally accelerated into an annular time of flight region, FIG. 16B shows conductive rings on a PCB substrate and FIG. 16C shows a microchannel plate ion detector which enables a radial potential to be maintained across the surface of the ion detector;

[0188] FIG. 17 shows trajectory classifications;

[0189] FIG. 18 shows an effective potential;

[0190] FIG. 19 shows the inner limit of an orbit;

[0191] FIG. 20 shows radial motion as a function of =t;

[0192] FIG. 21 shows orbital motion according to an embodiment;

[0193] FIG. 22A shows the trajectory of an ion injected into an annular ion guiding region without scanning the internal field and FIG. 22B shows the trajectory of an ion injected into an annular ion guiding region with a higher energy and also without scanning the internal field;

[0194] FIG. 23A shows a preferred method of injecting ions into the annular ion guiding region by splitting the injection region into a first and second sector and ensuring that ions initially experience a field free region when they are injected into the first sector and FIG. 23B shows the resulting ion trajectories after ions have moved from the first sector into the second sector and a radial field is restored in the first sector; and

[0195] FIG. 24A shows ions which have been injected into the mass analyser separating rotationally and FIG. 24B shows ions which have been injected into the mass analyser separating rotationally at a later time.

DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS

[0196] An arrangement will now be described with reference to FIG. 5. FIG. 5 shows an arrangement wherein a Time of Flight mass analyser is provided comprising two coaxial cylindrical electrodes with an annular ion guiding volume therebetween.

[0197] According to the preferred embodiment ions are confined radially between two coaxial cylinders which are held at different potentials Vouter and Vinner. The ion beam (which is preferably a packet of ions containing the different mass to charge ratio species to be analysed) is arranged to approach the outer cylinder where either a hole or a gap through which the ion beam may pass is preferably provided.

[0198] Ions entering the annular ion guiding volume preferably form stable circular orbits by increasing the field between the inner and outer cylinders once the ion beam has entered the device. In the absence of any other fields once inside the cylinders the ions preferably remain in orbit but will disperse in the axial direction according to their initial axial velocities. This is shown in FIG. 6A.

[0199] Referring now to FIG. 6B, once the ions are confined in stable circular orbits a pulsed voltage is applied to a grid electrode which is preferably placed inside the analyser between the two cylinders. In order to create the electric field functions required to achieve spatial focussing the inner and outer cylinders are preferably segmented and different voltages are preferably applied to each of the inner and outer segmented electrodes.

[0200] FIG. 6A shows how the inner and outer cylindrical electrodes may be axially segmented according to an embodiment. According to the preferred embodiment the inner and outer cylindrical electrodes are axially segmented in all of the embodiments described below, although for ease of illustration only some of the following drawings may omit the axial segmentation.

[0201] Referring again to FIG. 6B, the ions are orthogonally accelerated in an axial direction and preferably continue to rotate around the central electrode set but at the same time preferably begin to move along the axis of the Time of Flight mass analyser in a substantially helical manner.

[0202] It should be understood that time of flight dispersion only occurs in the axial direction and that the ions are confined radially to prevent transmission losses. As a result, the two coordinates in the preferred cylindrical device are decoupled in their behaviour.

[0203] FIG. 6B illustrates a simple embodiment with four principal planes P1,P2,P3,P4 which are directly analogous to the principal planes in a Wiley McLaren Time of Flight mass analyser as shown in FIG. 1. Spatial focussing is achieved in the same principle. However, in the geometry according to the embodiment as shown in FIG. 6B, the stable orbits in the radial direction prevent losses due to beam divergence and grid scattering at the grid boundaries.

[0204] A further advantage of the geometry according to the preferred embodiment is that when coupled to a pulsed packet of ions incoming to the spectrometer the entire ion packet may be captured into a stable orbit and utilised. If ions are stored in an upstream RF device between spectrometer acquisition cycles (pushes) then essentially a 100% duty cycle is potentially achievable with the preferred geometry.

[0205] According to the embodiment shown in FIGS. 6A and 6B ions may still be lost due to collisions with grid electrodes but the preferred embodiment advantageously has substantially higher transmission than conventional arrangements.

[0206] Other embodiments are also contemplated and will be described below which do not utilise grid electrodes and which are therefore even more advantageous compared with conventional arrangements.

[0207] It should be noted that the application of an orthogonal acceleration electric field or pulsing electric field after stable radial orbits are achieved is an important distinction over other known forms of mass analysers.

[0208] In particular, an Orbitrap mass analyser is known wherein a packet of ions from outside the device is pulsed into the mass analyser using deflection devices to change the direction of the beam to the axis of the spectrometer. Such deflection devices cause aberrations in the time of flight and distortions in the isochronous plane. These aberrations limit the resolution of such devices such that very long flight times are required before high resolutions can be achieved.

[0209] A particular advantage of the preferred embodiment is that the application of the acceleration field after stable orbits are achieved negates the need for deflection devices and enables resolution performances to be achieved in faster timescales similar to conventional orthogonal acceleration Time of Flight mass analysers.

[0210] It is an advantage of radially confined coaxial cylinder Time of Flight mass analysers according to embodiments of the present invention that long flight paths are possible without losses due to beam divergence losses. As such the preferred embodiment is ideally suited to multipass Time of Flight mass analyser geometries.

[0211] Various multipass geometries are contemplated and according to preferred embodiments contain a minimum number of grid electrodes in order to reduce losses at the principal planes.

[0212] FIGS. 7A and 7B show a preferred geometry according to an embodiment. According to this embodiment ions are injected and stabilised into one side of an axially symmetric device before a parabolic potential is applied along the length of the Time of Flight mass analyser. The parabolic potential acts to accelerate ions towards the centre of the spectrometer. The form of parabolic potential well preferably allows the ions to oscillate back and forth exhibiting simple harmonic motion. The more passes that the ions experience before detection the greater the resolution of the instrument.

[0213] Advantageously, ions may be stored in an upstream ion trap. Ions may be mass selectively ejected from the ion trap to sequentially release known mass ranges of ions to the analyser while storing others in the population. In this way a high resolution mass spectrum covering the entire mass range may stitched together from segments of the smaller acquired mass range.

[0214] The evolution of phase space illustrated in FIG. 7B shows that the isochronous plane is found in the centre of the device substantially at the bottom of the potential well. In fact there is a small deviation from the bottom which is a function of the inclination of the initial phase space ellipse but at typically envisaged device geometries this is a small effect.

[0215] According to an embodiment the ion detector may be placed or located in a region of the instrument where there is no axial field present.

[0216] According to an embodiment the ion detector may be located in an axial field free region of the instrument as will now be discussed with reference to FIGS. 8A-8D. FIGS. 8A-8D show an embodiment incorporating a combination of a Wiley McLaren and parabolic potential well sections. Each of FIGS. 8A-8D illustrate a different time in the acquisition cycle of the instrument.

[0217] Ions are preferably extracted from a coaxial geometry Time of Flight mass analyser according to an embodiment of the present invention and which incorporates a two field Wiley McLaren type source. The ions are orthogonally accelerated into a field free region and pass along through the field free region. The ions then experience a parabolic potential gradient (half a well) as shown in FIGS. 8A and 8B.

[0218] While ions are inside the parabolic section as shown in FIG. 8B, the other half of the well is preferably switched ON as shown in FIG. 8C and the ions are preferably allowed to oscillate for a desired number of times to increase the effective flight path of the instrument before ejection towards the ion detector as shown in FIG. 8D.

[0219] It will be noted from FIG. 8D that the isochronous plane is no longer at the base of the potential well. This is due to the amount of field free region required to bring the ion beam into isochronous spatial focus being exactly the distance between P3 and the detector in this case. Only half of the field free region is taken up on its outward trip to the right hand half of the parabolic potential well. When this half is switched OFF the ions of interest fly the remaining required field free region to be brought into isochronous spatial focus. It is the combination of a geometry that allows a portion of field free region along with a parabolic potential well allowing simple harmonic motion that makes such a multipass instrument possible. Without such a field free region there would be nowhere to position the detector without distortion of the electric fields.

[0220] If a higher degree of spatial focussing is required then the pulsed parabolic potential well may be contained in a field free region of a reflectron Time of Flight mass analyser. This further embodiment will now be described with reference to FIGS. 9A-9F.

[0221] The principle of operation according to this embodiment is similar to that described above with reference to FIGS. 8A-8D, but also includes a single pass mode as shown in FIGS. 9A-9C which does not include the pulsing of the parabolic potential well. Such a mode of operation is particularly useful when faster acquisition at lower resolution is required. The higher degree of spatial focussing enables the very highest possible resolution to be achieved for the lowest number of passes of the potential well.

[0222] As will be understood by those skilled in the art, the mass range of the Time of Flight mass analyser will reduce with the number of round trips made of the harmonic potential well. If the analyser is traversed a number of times N then the available mass range reduces with this value in the relation:

m.sub.max/m.sub.min=(N/(N1)).sup.2(1)

[0223] This could be seen as a disadvantage but the reduced mass range may be exploited by optimising the phase space conditions of the beam entering the analyser prior to acceleration. Generally ion beams are conditioned by a combination of RF focussing elements such as ring stacks, quadrupoles or higher order multipoles and electrostatic elements such as lenses and grids. Optimisation of initial conditions involves confining the beam closely to the optic axis. Most often the beam is confined tightly to the optic axis by using an RF only quadrupole but this device has a strong mass dependence in its focussing action. This means that while ions of a certain mass may be effectively squeezed to the optic axis, ions of higher mass are less strongly confined and ions of lower mass may be unstable in the device or pick up excessive energy from the RF field.

[0224] Accordingly, the transmission of a limited mass range to the analyser determined by the number of round trips enables optimisation of phase space characteristics for the masses contained within the reduced mass range for best possible instrument resolution.

[0225] WO 2011/154731 (Micromass) describes how an ion beam may be expanded to optimise phase space conditions in a conventional two stage Wiley McLaren instrument. WO 2011/154731 discloses how the limiting turnaround time aberration in a properly expanded beam scales with the acceleration potential difference seen by the beam rather than the electric field in that region.

[0226] The preferred embodiment of the present invention allows for perfect aberration free beam expansion by allowing a packet of ions which has been injected into the analyser to rotate around the central electrode for as long as desired before orthogonal acceleration. The analyser is entirely field free in the axial direction before the acceleration pulse is applied. This allows free expansion due to the ions initial velocity. The process is essentially similar to having a variable flight distance from the transfer optics to the Time of Flight mass analyser. As the ions rotate and expand the phase space ellipse becomes more elongated and the beam picks up more of the acceleration potential when it is applied. So long as the analyser has a good enough spatial focussing characteristic then resolution will improve as the beam is allowed to expand. By prudent placing of an aperture plate (or beam stop) within the Time of Flight mass analyser acceleration region the maximum size that the beam can axially expand to may be limited to the spatial focussing characteristic of the analyser. If once the position of the beam stop is reached the ions are allowed to rotate further prior to acceleration, the phase space will take the form of a truncated ellipse getting thinner in the velocity direction the longer the rotation takes. This is illustrated in FIG. 10.

[0227] By varying the delay time greater resolutions may be reached at the expense of some ion losses. This may be thought of as analogous to the technique of delayed extraction in MALDI instruments whereby the ions are allowed to leave the target plate and adopt positions correlated with their initial velocity in the ion source prior to extraction into the analyser. The correlation of ion velocity and position is very high due to the desorption event being defined by a plane. The delayed extraction according to embodiments of the present invention does not have such complete position/velocity correlation but nevertheless high degrees of ion focussing can be achieved and can be further optimised for the mass range of interest being injected into the analyser i.e. the delay time may be set to allow the central mass in the injected range to just reach the position of the beam stop (i.e. fill to the level before spatial focussing degrades the resolution) before extraction takes place.

[0228] US-546495 (Cornish) discloses using a curved field reflectron to bring ions of wide kinetic energy difference created by post source decay (PSD) in MALDI Time of Flight mass analyser instruments. According to an embodiment of the present invention such an arrangement may be utilised to give a first acceleration stage with good spatial focussing and the field free region necessary for suitable positioning of the ion detector.

[0229] As mentioned above, further embodiments of the present invention are contemplated wherein no grid electrodes are utilised. The radial confinement afforded by the stable orbit means that the ions adopt a narrow range of radial positions. This means that it is possible to make the entire system gridless and still maintain good spatial focussing while avoiding the disturbance in the axial electric fields and ion losses that these elements introduce. Gridless Time of Flight mass analysers without the radial stability of the present invention suffer from the defocusing effect of the electric fields caused by overfilling of the ion optical elements ultimately limiting device sensitivity and resolution.

[0230] An example of a gridless electrode arrangement according to an embodiment of the present invention is shown in FIG. 11. In this case the electric potentials to be pulsed are shown as dotted lines but the order and nature of their pulsing and the phase space evolution is similar to that described with reference to FIGS. 8A-8D. Elimination of grid electrodes has a further advantage in that is simplifies the method of construction as the device may consist of two concentric segmented cylinders assembled independently rather than having common mechanical parts (e.g. grid electrodes) in contact with both outer and inner assemblies within the internal space between the two.

[0231] Modelling of a coaxial Time of Flight mass analyser according to an embodiment of the present invention was performed. Results from an analytic system were compared with resulting from a SIMION simulation of a coaxial Time of Flight mass analyser geometry according to the preferred embodiment.

[0232] FIG. 12 shows the Time of Flight mass analyser geometry used for the modelling where the mean ion start plane is at the centre of the pusher region of length L1=40 mm. The voltage V1 equals 1000 V.

[0233] The acceleration region L2 was set at 50 mm and voltage V2 was set at 5000 V. The various regions are bounded by grid electrodes while the parabolic regions are not grid bounded. The distance Lp was modelled as being 99 mm and Vp was set at 10,000 V. The left hand parabola (LHP) is ramped up after ions are in the right hand parabola (RHP). The RHP is ramped down while the ions are in the LHP after the desired number of passes have occurred.

[0234] In the python model the total field free distance is a variable that can be solved while in the SIMION simulation the ions are recorded at a fixed detector plane distance. These ions can then be imported into the python model and can be solved for a variable field free region, hence both approaches can be brought into focus.

[0235] FIG. 13 shows the co-axial geometry used in the SIMION modelling. The radius of the inner cylinder Rin was set at 10 mm and the outer cylinder radius Rout was set at 20 mm. Accordingly, Rgap equals 10 mm.

[0236] The axial electrode segments were arranged to be 1 mm wide with 1 mm gaps therebetween. Grid electrodes were modelled as being located between segments and voltages were modelled as being applied to give linear voltage drops across the first two regions and quadratic potentials in the parabolic regions.

[0237] A potential difference was applied between the inner and the outer cylinders to give radial confinement. In the results presented +650 V was applied to the outer cylinder and the inner cylinder is at the same potential as the grids.

[0238] For singly charged ions having a mass to charge ratio of 500 with 500 eV of radial KE and +650 V being applied to the outer cylinder gives good radial confinement. Significant radial KE is required to retain confinement within the parabolic regions which give radial divergence.

[0239] For the first system the initial ion conditions were 1 mm position delta (+/0.5 mm), Gaussian velocity spread with a 5 m/s standard deviation, no initial ion drift, 8 passes through the parabolic regions (1 pass is into then back out of a single parabola) and 10 kV on the parabolas. The results are shown in FIG. 14.

[0240] The total FFR is 1203 mm for the analytic system with 70.712 s drift time. For the Time of Flight mass analyser according to the preferred embodiment the FFR is 1619 mm with a 79.617 s drift time. The resolution performance of the Time of Flight mass analyser according to an embodiment of the present invention is comparable with the analytic system.

[0241] If the initial phase space is set smaller and more passes through the parabolas are allowed then the resolution according to the preferred embodiment is further improved. For this system the initial ion conditions were 0.2 mm position delta (+/0.1 mm), Gaussian velocity spread with a 1 m/s standard deviation, no initial ion drift, 32 passes through the parabolic regions (1 pass is into then back out of a single parabola) and 10 kV on the parabolas.

[0242] The analytic system had a FFR of 1203 mm whereas the FFR according to the preferred system was 1630 mm. The resolution of the analytic system was 189,000 compared with 170,000 resolution for system according to the preferred embodiment.

[0243] It will be appreciated that a Time of Flight mass analyser having a potential resolution of 170,000 represents a very significant advance in performance compared with current state of the art commercial Time of Flight mass analysers.

[0244] Although the analytic and SIMION systems are not in exact agreement it is apparent that the preferred embodiment is able to achieve about 90% of the analytic resolution. The flight time for the analytic system was 191 s whereas the flight time for the preferred embodiment was 200 s as shown in FIG. 15. In both cases the flight time is not excessively long (12 GHz TDC detector).

Unique Path Through Multipass Co-Axial Cylinder TOF

[0245] It is a distinct disadvantage of known multipass Time of Flight mass spectrometers that the mass range reduces as the number of passes through the analyser increases. This is because it is impossible to distinguish a faster lower mass ion from a slower higher mass ion which may have made a lower number of analyser passes. Consequently, only a small subset of the mass range to be analysed may be injected into the spectrometer so as to avoid aliasing at the chosen number of roundtrips of the analyser.

[0246] An important feature of a preferred embodiment of the present invention is that a unique path is provided for all ions of all masses so that the entire mass range may be covered in a single acquisition cycle. The present invention therefore represent a significant improvement in the art.

[0247] Ions are preferably injected into a segmented coaxial cylinder Time of Flight mass spectrometer using a switched sector with no axial field. The ions are preferably injected such that they describe circular trajectories in the cylindrical pusher region of the spectrometer. The ions are allowed to rotate around the central electrode set and expand to fill the pusher so that they see a large voltage drop when the extraction field is subsequently activated to minimise the turnaround time.

[0248] The extraction field is preferably activated to give an axial and radial impetus to the circularly rotating ion beam. The axial field is preferably created using a quadratic potential function so that the ions preferably exhibit substantially simple harmonic motion in the z-direction (the direction of Time of Flight analysis). The radial field is also pulsed at the same time such that the ions no longer describe perfect circular orbits but rather they begin to describe eccentric orbits which allow a variation in the radial position as they traverse the analyser. The ions preferably exhibit radial oscillations which are independent in frequency to those in the axial direction. In other embodiments the ions may describe unstable trajectories sending them in an inward or outward direction. In either case it is desired that the ions describe a unique path in the analyser describing a number of oscillations in the z direction before they strike an ion detector which is preferably placed inside the analyser perpendicular to the z axis and at a position preferably corresponding to the isochronous plane.

[0249] It is an advantage of the present invention that the ions are free to expand in the angular coordinate as the ion detector may take the form of an annulus so capturing all ions regardless of i.e. no constraint or control of the ions is preferably required in the direction.

[0250] The segmented construction of the device and the inherent decoupling of the applied axial and radial field components allows for independent control of radial and axial motion which is not possible using cylindrical electrodes of solid construction that can only satisfy the boundary conditions for a fixed ratio of radial to axial field strength. A particularly preferred embodiment of the present invention is shown in FIG. 16A.

[0251] Ions are injected between an outer segmented electrode set O1 and an inner segmented injection electrode set I1 where they are allowed to rotate and axially expand by virtue of their thermal velocity (from the ion source).

[0252] Pulsed radial and axial fields are then preferably applied and move the ion beam into the central portion of the analyser where they oscillate with radial amplitude R and axial amplitude z. The injection segment of the analyser may be narrower than that of the central part so as to minimise aberrations on entry to the switched sector region. According to an embodiment the axial field is preferably raised further when the ions first enter the main body of the device so as to prevent the ions from striking the narrower injection region due to radial oscillation imparted by the pulsed component of the radial field. This gives a small mass dependence in Time of Flight trajectory but does not change the position of the isochronous plane P1. In order to control the fringe fields at the ends of the device and at the position of the ion detector some optical components may be incorporated that closely follow the boundary conditions of the desired analytical field F1, F2 and the surfaces of the ion detector D. These may take the form of conductive rings on PCB substrates to which are applied the correct voltage (FIG. 16B). In the case of a microchannel plate detector its resistive nature may be utilised and the boundary conditions may be satisfied by applying radial voltages V1 and V2 between its inner and outer regions as shown in FIG. 16C.

[0253] According to the preferred embodiment the ions preferably miss the ion detector for a predetermined number of passes by controlling the frequency, amplitude and phasing of the radial oscillations.

Derivation of Equations of Motion

[0254] The equations of motion may be derived using the Lagrangian formulation. The Lagrangian is the difference between the kinetic energy and the potential energy. In cylindrical polar coordinates with a time-independent and cylindrically symmetric potential this is:

L=TV=m[(r).sup.2+{dot over (r)}.sup.2+.sup.2]qU(r,z)(2)

[0255] The three Euler-Lagrange equations are:

[00001]$\begin{array}{cc}\frac{}{t}.Math.\frac{L}{{\stackrel{.}{q}}_i}-\frac{L}{q_i}=0& \left(3\right)\end{array}$

one for each of the three q.sub.i cylindrical coordinates r, and z. For the class of potentials that are of interest:

[00002]$\begin{array}{cc}m\left(\stackrel{\mathrm{.Math.}}{r}-r.Math..Math.{\stackrel{.}{}}^2\right)=-q.Math.\frac{U\left(r,z\right)}{r}& \left(4\right)\\ m.Math.\stackrel{\mathrm{.Math.}}{z}=-q.Math.\frac{U\left(r,z\right)}{r}& \left(5\right)\\ \frac{}{t}.Math.\left({\mathrm{mr}}^2.Math.\stackrel{.}{}\right)=0& \left(6\right)\end{array}$

[0256] Some general conclusions can be drawn. Firstly, the motion in the z direction is decoupled from orbital motion in the (r, ) plane when the potential can be written in the form:

U(r,z)=U.sub.r(r)+U.sub.z(z)(7)

[0257] Second, Eqn. 6, which expresses conservation of angular momentum L.sub.z for motion around the z axis can be rewritten as:

[00003]$\begin{array}{cc}\stackrel{.}{}\left(t\right)=\frac{L_z}{{\mathrm{mr}}^2\left(t\right)}& \left(8\right)\end{array}$

which implies that unless is constant (L.sub.z=0 corresponds to pure radial motion), or the radius is constant (pure circular motion), then motion in r and q is coupled. When Eqn. 7 is satisfied, the problem reduces to the differential equations for the radial variable and variable which are respectively:

[00004]$\begin{array}{cc}m\left(\stackrel{\mathrm{.Math.}}{r}-\frac{L_z^2}{m^2.Math.r^3}\right)=-q.Math.\frac{U_r}{r}& \left(9\right)\\ m.Math.\stackrel{\mathrm{.Math.}}{z}=-q.Math.\frac{U_z}{z}& \left(10\right)\end{array}$

and given r(t), (t) can be obtained by integrating Eqn. 8.

[0258] The radial equation of motion Eqn. 9 can be reformulated as follows:

[00005]$\begin{array}{cc}m.Math.\stackrel{\mathrm{.Math.}}{r}=-q.Math.\frac{{\tilde{U}}_r}{r}& \left(11\right)\end{array}$

where the effective radial potential includes a centrifugal term:

[00006]$\begin{array}{cc}{\tilde{U}}_r\left(r\right)=U_r\left(r\right)+\frac{L_z^2}{2.Math.{\mathrm{mqr}}^2}& \left(12\right)\end{array}$

The energy E.sub.r is conserved:

[00007]$\begin{array}{cc}{E}_{r.Math..Math.}=\frac{1}{2}.Math.m.Math.{\stackrel{.}{r}}^2+q.Math.{\tilde{U}}_r\left(r\right)& \left(13\right)\end{array}$

[0259] An initial condition that is of particular interest occurs when ions attain their initial velocity by acceleration through a potential drop U. For simplicity, it is assumed that the injection radius is R.sub.0 and the initial radial velocity r(0)=0. In this case the angular momentum satisfies:

L.sub.z.sup.2=2mqR.sub.0.sup.2U(14)

so that:

[00008]$\begin{array}{cc}{\tilde{U}}_r\left(r\right)=U_r\left(r\right)+\frac{R_0^2.Math..Math..Math.U}{r^2}& \left(15\right)\end{array}$

which is explicitly independent of q and m. It will be noted that unusually for a potential, .sub.r changes with the initial conditions (R.sub.0 and U or, equivalently, the orbital angular momentum L.sub.z). However, for fixed U.sub.r(r), the mapping:

[00009]$\begin{array}{cc}{R}_0->R_0^{},.Math..Math.U->.Math..Math.U.Math.\frac{R_0^2}{R_0^2}& \left(16\right)\end{array}$

leaves the angular momentum and the effective potential unchanged. Stable circular orbits may be obtained when it is possible to choose the quantity R.sub.0.sup.2U in such a way that r=R.sub.0 is a minimum of the effective potential .sub.r(r).

Orbital Differential Equation

[0260] A differential equation for the orbit r() can also be obtained. First from Eqn. 8 the following can be obtained:

[00010]$\begin{array}{cc}d.Math..Math.=\frac{L_z}{{\mathrm{mr}}^2}.Math.\mathrm{dt}& \left(17\right)\end{array}$

and thence:

[00011]$\begin{array}{cc}\frac{d}{\mathrm{dt}}=\frac{L_z}{{\mathrm{mr}}^2}.Math.\frac{d}{d.Math..Math.}& \left(18\right)\end{array}$

which enables the time derivative to be eliminated in favour of a derivative:

[00012]$\begin{array}{cc}m.Math.\stackrel{\mathrm{.Math.}}{r}=m.Math.\frac{d^2.Math.r}{{\mathrm{dt}}^2}=\frac{L_z^2}{m}.Math.\frac{1}{r^2}.Math.\frac{d}{d.Math..Math.}.Math.\left(\frac{1}{r^2}.Math.\frac{\mathrm{dr}}{d.Math..Math.}\right)=-2.Math.{\mathrm{qR}}_0^2.Math..Math..Math.{\mathrm{Uu}}^2.Math.\frac{d^2.Math.u}{d.Math..Math.{}^2}& \left(19\right)\end{array}$

where Eqn. 14 has been used and introduced the new variable u=1/r. Noting that:

[00013]$\begin{array}{cc}\frac{d}{\mathrm{dr}}=-u^2.Math.\frac{d}{\mathrm{du}}& \left(20\right)\end{array}$

the equation of motion Eqn. 11 becomes a differential equation for the orbit:

[00014]$\begin{array}{cc}\frac{d^2.Math.u}{d.Math..Math.{}^2}=\frac{-1}{2.Math.R_0^2.Math..Math..Math.U}.Math.\frac{d.Math.{\tilde{U}}_r\left(l/u\right)}{\mathrm{du}}& \left(21\right)\end{array}$

[0261] With initial conditions, if the effective potential .sub.r is independent of q and m then the same will be true of u() and therefore r().

Time Dependence and Orbital Period

[0262] Ions are initially set up in a circular orbit. The times at which bounded orbits reach various radii are of interest. For central forces the orbit is symmetric about each of its turning points, and the first traversal from r=R.sub.max to r=R.sub.min (or vice-versa) enables relevant equations to be derived. Furthermore t(r) is single value in this range.

[0263] Starting from the energy conservation Eqn. 13 then since the starting point is a circular orbit and a pulse in the field at t=0 then the initial conditions will be r(0)=R.sub.max and {dot over (r)}(0)=0. Alternatively, it is possible to start at r=R.sub.min but the conclusions would be essentially the same. The following equation can therefore be written:

[00015]$\begin{array}{cc}q.Math.{\tilde{U}}_r\left(R_{\max }\right)=\frac{1}{2}.Math.m.Math.{\stackrel{.}{r}}^2+q.Math.{\tilde{U}}_r\left(r\right)& \left(22\right)\end{array}$

which can be rearranged as:

[00016]$\begin{array}{cc}\stackrel{.}{r}=-\sqrt{\frac{2.Math.q}{m}.Math.\left({\tilde{U}}_r\left(R_{\max }\right)-{\tilde{U}}_r\left(r\right)\right)}& \left(23\right)\end{array}$

where the negative square root is taken since it is known that {dot over (r)}<0 in the part of the trajectory that is relevant. This may be rewritten in the following form:

[00017]$\begin{array}{cc}\mathrm{dt}=-\sqrt{\frac{m}{2.Math.q}}.Math.\frac{\mathrm{dr}}{\sqrt{\left({\tilde{U}}_r\left(R_{\max }\right)-{\tilde{U}}_r\left(r\right)\right)}}& \left(24\right)\end{array}$

which can be integrated to give:

[00018]$\begin{array}{cc}t\left(r\right)=\sqrt{\frac{m}{2.Math..Math.q}}.Math.{}_r^{R_{\max }}.Math.{\mathrm{dr}\left({\tilde{U}}_r\left(r_{\max }\right)-{\tilde{U}}_r\left(r\right)\right)}^{-1/2}\sqrt{\frac{m}{q}}.Math..Math.\left(r\right)& \left(25\right)\end{array}$

where for convenience q and in have been introduced and the independent function (r):

[00019]$\begin{array}{cc}\left(r\right)=\frac{1}{\sqrt{2}}.Math.{}_r^{R_{\max }}.Math.{\mathrm{dr}\left[{\tilde{U}}_r\left(R_{\max }\right)-{\tilde{U}}_r\left(r\right)\right]}^{-1/2}& \left(26\right)\end{array}$

[0264] The period of the radial orbit is the time taken to reach R.sub.min and return to R.sub.max which is:

[00020]$\begin{array}{cc}{T}_r=2.Math..Math.t\left(R_{\min }\right)=2.Math.\sqrt{\frac{m}{q}}.Math.\left(R_{\min }\right)& \left(27\right)\end{array}$

[0265] Unfortunately, for the class of potentials that are of interest, this integral cannot be performed analytically. However, numerical solutions may be obtained in a straightforward manner.

Decoupled Solutions of Laplace's Equation

[0266] It is desired to find the general solution of Laplace's equation with cylindrical symmetry and the constraint that the field at fixed radius r is quadratic in the axial direction z.

[0267] Laplace's equation in cylindrical polar coordinates may be written as follows:

[00021]$\begin{array}{cc}{}^2.Math.U\left(r,,z\right)=\left(\frac{1}{r}.Math.\frac{}{r}.Math.r.Math.\frac{}{r}+\frac{1}{r^2}.Math.\frac{{}^2}{{}^2}+\frac{{}^2}{z^2}\right).Math.U\left(r,,z\right)=0& \left(28\right)\end{array}$

[0268] Since solutions with cylindrical symmetry are desired the angular dependence can be dropped to give (for all ):

[00022]$\begin{array}{cc}\left[\frac{1}{r}.Math.\frac{}{r}.Math.r.Math.\frac{}{r}+\frac{{}^2}{z^2}\right].Math.U\left(r,z\right)=0& \left(29\right)\end{array}$

[0269] A solution of the form is desired:

U(r,z)=a(r)z.sup.2+b(r)(30)

which is quadratic in z for fixed r. Substituting this into Eqn. 29 gives:

[00023]$\begin{array}{cc}{z}^2.Math.\frac{1}{r}.Math.\frac{}{r}.Math.r.Math.\frac{}{r}.Math.a\left(r\right)+2.Math..Math.a\left(r\right)+\frac{1}{r}.Math.\frac{}{r}.Math.r.Math.\frac{}{r}.Math.b\left(r\right)=0& \left(31\right)\end{array}$

[0270] In order for this equation to be satisfied for all values of z the first term must vanish:

[00024]$\begin{array}{cc}{z}^2.Math.\frac{1}{r}.Math.\frac{}{r}.Math.r.Math.\frac{}{r}.Math.a\left(r\right)=0& \left(32\right)\end{array}$

which can be integrated directly to give:

[00025]$\begin{array}{cc}a\left(r\right)=a_0.Math.\ln \left(r/r_0\right)+\frac{k}{2}& \left(33\right)\end{array}$

wherein r.sub.0 is an arbitrary constant with dimensions of length which is introduced to keep the argument of the logarithm explicity dimensionless. Substituting back into Eqn. 31 yields:

[00026]$\begin{array}{cc}\frac{}{r}.Math.r.Math.\frac{}{r}.Math.b\left(r\right)=-2.Math..Math.a_0.Math.r.Math..Math.\ln \left(r/r_0\right)-\mathrm{kr}& \left(34\right)\end{array}$

which can be integrated once more to give:

[00027]$\begin{array}{cc}\frac{}{r}.Math.b\left(r\right)=a_0.Math.r\left[\frac{1}{2}-\ln \left(r/r_0\right)\right]-\frac{k}{2}.Math.r+b_0/r& \left(35\right)\end{array}$

and again:

[00028]$\begin{array}{cc}b\left(r\right)=\frac{a_0.Math.r^2}{2}.Math.\left(1-\ln \left(r/r_0\right)\right)-\frac{k}{4}.Math.r^2+b_0.Math.\ln \left(r/r_0\right)+b_1& \left(36\right)\end{array}$

The general solution may be written:

[00029]$\begin{array}{cc}U\left(r,z\right)=\frac{k}{2}.Math.\left(z^2-r^2/2\right)+b_0.Math.\ln \left(r/r_0\right)+b_1+a_0\left[z^2.Math.\ln \left(r/r_0\right)+\frac{r^2}{2}.Math.\left(1-\ln \left(r/r_0\right)\right)\right]& \left(37\right)\end{array}$

[0271] Setting a.sub.0=0 so that the axial motion is decoupled from motion in the r, plane, then the potential is:

[00030]$\begin{array}{cc}U\left(r,z\right)=\frac{k}{2}.Math.\left(z^2-r^2/2\right)+b_0.Math.\ln \left(r/r_0\right)+b_1& \left(38\right)\end{array}$

with a unique z-independent stationary point in the radial direction at:

[00031]$\begin{array}{cc}{R}_m=\sqrt{\frac{2.Math..Math.b_0}{k}}& \left(39\right)\end{array}$

which is a maximum for k>0. This field can approximated using a series of closely spaced (in z) pairs of coaxial annular electrodes of arbitrary outer and inner radius R.sub.1 and R.sub.2. The potentials that must be applied to the electrodes at axial position z are:

[00032]$\begin{array}{cc}{U}_1\left(z\right)=\frac{k}{2}.Math.\left(z^2-R_1^2/2\right)+b_0.Math.\ln \left(R_1/r_0\right)+b_1.Math..Math.U_2\left(z\right)=\frac{k}{2}.Math.\left(z^2-R_2^2/2\right)+b_0.Math.\ln \left(R_2/r_0\right)+b_1& \left(40\right)\end{array}$

[0272] There is no mathematical constraint on the k, b.sub.0, b.sub.1 or consequently R.sub.m that can be produced in this way. The equations of motion corresponding to the potential Eqn. 37 are:

[00033]$\begin{array}{cc}\left(\stackrel{\mathrm{.Math.}}{r}-r.Math..Math.{\stackrel{.}{}}^2\right)=\frac{q}{m}\left[\frac{k}{2}.Math.r-\frac{b_0}{r}\right]& \left(41\right)\\ \stackrel{\mathrm{.Math.}}{z}=-\frac{\mathrm{qk}}{m}.Math.z& \left(42\right)\\ \frac{}{t}.Math.\left(r^2.Math.\stackrel{.}{}\right)=0.& \left(43\right)\end{array}$

Axial Motion

[0273] When k=0, Eqn. 42 describes simple harmonic motion in the z direction. The solution is well known. For an ion with initial position z(0) and z-velocity z(0):

[00034]$\begin{array}{cc}z\left(t\right)=z\left(0\right).Math.\cos .Math..Math.{}_z.Math.t+\frac{\stackrel{.}{z}\left(0\right)}{{}_z}.Math.\sin .Math..Math.{}_z.Math.t& \left(44\right)\end{array}$

where the angular frequency .sub.z={square root over (qk/m)}. The period is T=2/.sub.z

Circular Orbits

[0274] To obtain circular orbits (ignoring axial motion) it is required that r=r=0. From Eqn. 43 it may be inferred that {umlaut over ()}=0 which implies that these trajectories have constant angular velocity with, from Eqn. 41:

[00035]$\begin{array}{cc}{\stackrel{.}{}}^2=\frac{q}{m}\left[\frac{b_0}{R_0^2}-\frac{k}{2}\right]& \left(45\right)\end{array}$

for a circular orbit of radius R.sub.0. This expression is valid as long as R<R.sub.m.

The General Orbit

[0275] To treat more general orbits the effective radial potential Eqn. 15 for the particular potential Eqn. 38 may be considered. By choosing r(0)=0 the trajectory may be started at a radial turning point or stationary point. Ignoring irrelevant constant (or purely z dependent) terms:

[00036]$\begin{array}{cc}{\tilde{U}}_r\left(r\right)=-\frac{k}{4}.Math.r^2+b_0.Math.\ln \left(r/r_0\right)+\frac{R_0^2.Math..Math..Math.U}{r^2}& \left(46\right)\\ \frac{{\tilde{U}}_r}{r}=-\frac{k}{2}.Math.r+\frac{b_0}{r}-2.Math.\frac{R_0^2.Math..Math..Math.U}{r^3}& \left(47\right)\end{array}$

and therefore stationary points at R.sub.S satisfying:

[00037]$\begin{array}{cc}-\frac{k}{2}.Math.R_S^4+b_0.Math.R_S^2-2.Math.R_0^2.Math..Math..Math.U=0..Math..Math.\mathrm{or}& \left(48\right)\\ R_S^2\frac{b_0}{k}.Math.\left(1\sqrt{1-\frac{4.Math.k.Math..Math.R_0^2.Math..Math..Math.U}{b_0^2}}\right)& \left(49\right)\end{array}$

which has two distinct solutions as long as:

b.sub.0>2{square root over (kU)}R.sub.0(50)

taking k, b.sub.0, U>0. The limiting behaviour of the effective potential Eqn. 46 is:

[00038]$\begin{array}{cc}\underset{r.fwdarw.0}{\lim }.Math.{\tilde{U}}_r=\frac{R_0^2}{r^2}.Math..Math..Math.U.Math..Math.\underset{r.fwdarw.}{\lim }.Math.{\tilde{U}}_r=-\frac{k}{4}.Math.r^2& \left(51\right)\end{array}$

which is large positive for small r and large negative for large r so that the stationary points R.sub.S and R.sub.S+ defined by Eqn. 49 must be a minimum and maximum respectively. Consequently, the condition Eqn. 50 is necessary for the existence of bounded orbits which must also satisfy r<R.sub.S+. The radius at perigree and apogee of bounded orbits may be denoted as R.sub.min and R.sub.max respectively. It is apparent that:

.sub.r(R.sub.min)=.sub.r(R.sub.max) and R.sub.max=R.sub.0(52)

[0276] The nature of the trajectory with starting point r=R.sub.0 is partly determined by the sign of the gradient of the effective potential Eqn. 47 at r=R.sub.0. In particular, if the gradient (times R.sub.o):

[00039]$\begin{array}{cc}{R}_0.Math.{\tilde{U}}_r^{}\left(r\right).Math.{|}_{r=R_0}=b_0-2.Math..Math..Math.U-\frac{k}{2}.Math.R_0^2& \left(53\right)\end{array}$

is positive, the starting point is a radial maximum and the trajectory must be bounded. If the gradient is negative, then the starting point is a radial minimum and the orbit is bounded if (and only if) R.sub.OR.sub.S+ and U.sub.r(R.sub.O)U.sub.r(R.sub.S+). If the gradient is zero then the conditions for a circular orbit are satisfied (stable if R.sub.O=R.sub.S and unstable if R.sub.O=R.sub.S+).

[0277] FIG. 17 shows the trajectories produced at points in the (R.sub.0, b.sub.0) plane for fixed k and U. In the regions above the straight line b.sub.0>2{square root over (kU)} R.sub.0 the potential has two stationary points (a minimum and a maximum). In the region above the curved line

[00040]$b_0>2.Math..Math..Math.U+\frac{k}{2}.Math.R_0^2$

the trajectory is bounded and starts at a radial maximum. The straight and curved lines meet at the point:

[00041]$\begin{array}{cc}{R}_0=2.Math.\sqrt{\frac{.Math..Math.U}{k}},b_0=4.Math..Math..Math.U& \left(54\right)\end{array}$

which corresponds to an unstable circular trajectory at an inflection point of the effective potential. The boundary between bound and unbound trajectories in the region below R.sub.0=R.sub.S is not shown on this plot. FIG. 17 shows trajectory classification for k=810.sup.4 Vm.sup.2 and U=1000 V. Above the straight line the effective potential has a minimum. Above the curved line the starting point is the radial maximum of a bound trajectory.

[0278] An example of an effective potential corresponding to a bound trajectory is shown in FIG. 18 with parameters k=810.sup.4 Vm.sup.2, R.sub.0=R.sub.max=0.075 m, b.sub.0=5000 V and U=1000 V. The stationary points of the potential are at R.sub.S=0.048 m and R.sub.S+=0.350 m (off scale). R.sub.min=0.034 m. Starting at r=R.sub.0=R.sub.max ions oscillate between R.sub.min and R.sub.max.

[0279] FIG. 19 shows R.sub.min as a function of b.sub.0 for the orbit corresponding to k=810.sup.4 Vm.sup.=2 with U=1000 V and R.sub.0=0.075 m. As b.sub.0 increases (and with it the attractive part of the potential), R.sub.min decreases. It will be noted that the trajectories towards the right of this plot are highly eccentric.

Three Dimensional Trajectories

[0280] It is desired to find a set of trajectories which oscillate back and forth axially through the mass spectrometer, missing the ion detector for a predetermined number of passes N10 and hit the ion detector on the final pass N. Considering the axial equation of motion Eqn. 44 with the added assumption that the ions start with no axial velocity i.e. z(0)=0. For brevity we shall also write Z.sub.0z(0).

z(t)=Z.sub.O cos .sub.zt(55)

[0281] This orbit passes the ion detector at times:

[00042]$\begin{array}{cc}{t}_n=\frac{\left(2.Math.n-1\right).Math.}{2.Math.{}_z},n=1,2.Math..Math.\mathrm{.Math.}& \left(56\right)\end{array}$

[0282] It is assumed for simplicity that the axial extent of the ion detector W.sub.d is small compared with the axial extent of the orbit i.e. W.sub.d<<2Z.sub.0. As ions pass the ion detector the ions have velocity z=Z.sub.0.sub.z so the time taken to pass the ion detector is approximately:

[00043]$\begin{array}{cc}.Math..Math.T_d=\frac{W_d}{Z_0.Math.{}_z}=\frac{W_d}{Z_0.Math.\sqrt{k}}.Math.\sqrt{\frac{m}{q}}& \left(57\right)\end{array}$

[0283] It is desired to find radial trajectories that satisfy r(t)>H.sub.d for |tt.sub.n|<T.sub.d/2 when n<N and r(t)<H.sub.d for t=t.sub.N. It is desired to know the times at which the radial orbit reaches the critical radius r=H.sub.d.

[0284] Ignoring initially the finite axial extent of the ion detector, it is noted that R.sub.min is achieved at odd multiples of one half of the radial period, while z=0 occurs at odd multiples of one quarter of the axial period. Assuming that R.sub.min<H.sub.d, ions are guaranteed to hit the ion detector when r=R.sub.min and z=0 simultaneously. This occurs for all pairs of positive integers j, n satisfying:

[00044]$\begin{array}{cc}\left(2.Math.j-1\right).Math.\frac{T_r}{2}=\left(2.Math.n-1\right).Math.\frac{T_z}{4}& \left(58\right)\end{array}$

which may also be written:

[00045]$\begin{array}{cc}\frac{2.Math.j-1}{2.Math.n-1}=\frac{1}{2}.Math.\frac{T_z}{T_r}& \left(59\right)\end{array}$

From Eqn. 27 the condition is therefore:

[00046]$\begin{array}{cc}\frac{2.Math.j-1}{2.Math.n-1}=\frac{}{2}.Math.\frac{1}{\sqrt{k}.Math.r\left(R_{\min }\right)}& \left(60\right)\end{array}$

which is independent of q and m as it must be, and (R.sub.min) is the integral Eqn. 26:

[00047]$\begin{array}{cc}\left(R_{\min }\right)=\frac{1}{\sqrt{2}}.Math.{}_{R_{\min }}^{R_{\max }}.Math.{\mathrm{dr}\left[{\tilde{U}}_r\left(R_{\max }\right)-{\tilde{U}}_r\left(r\right)\right]}^{-1/2}& \left(61\right)\end{array}$

[0285] FIG. 18 shows the effective potential with parameters k=810.sup.4 Vm.sup.2, R.sub.11=R.sub.max=0.075 m, b.sub.o=5000 V and U=1000 V. The stationary points of the potential are at R.sub.s=0.048 m and R.sub.s+=0.350 m (off scale). R.sub.min=0.034 m.

[0286] To fulfill the condition that the detector is missed N1 times for fixed k and U a point must be chosen in (b.sub.0, R.sub.0) space near which Eqn. 60 is satisfied for n=N but away from points at which the condition is met for 1<n<N.

[0287] FIGS. 19 and 20 illustrate the trajectory corresponding to N=7, j.sub.max=19 with an injection radius of r=0.065 m which passes the ion detector axially six times finally hitting on the seventh pass. FIG. 19 shows the inner limit of orbit for k=810.sup.4 Vm.sup.2, U=1000 V and R.sub.0=0.075 m.

[0288] FIG. 20 shows radial motion as a function of =t{square root over (q/m)} for k=810.sup.4 Vm.sup.2, U=1000 V, b.sub.0=3700 V and R.sub.0=0.065 m. The horizontal line at r=0.039 m represents a possible detector surface. Ions pass the ion detector axially six times, finally hitting on the seventh pass after 18.5 radial cycles. The vertical lines correspond to values of for which ions pass through the plane z=0. The to pass a detector with width W.sub.d=0.01 m is invisible on the scale of this plot.

[0289] FIG. 21 shows orbital motion for k=810.sup.4 Vm.sup.2, U=1000 V, b.sub.0=3700 V and R.sub.0=0.065 m.

[0290] According to an alternative embodiment the ion trajectory may start near an inflection point of effective radial potential and allow ions to spiral outwards to an annular detector.

[0291] According to another embodiment a radially bound trajectory may start at R.sub.min rather than R.sub.max. In this case the injection radius would be lower than the outer detector radius.

Method of Ion Injection into Co-Axial Cylinder TOF

[0292] A less preferred method of injecting ions into the spectrometer so that they achieve a stable trajectory has been shown and described above with reference to FIG. 5. According to this less preferred embodiment stable trajectories may be achieved by reducing the voltage on the inner electrode with respect to the outer electrode as the ions enter the device. This approach requires a packet of ions of limited temporal distribution to be pulsed into the device. Ions injected in this way adopt a range of radial positions that have a slight mass dependency. This is not ideal since it is required that all ions experience the same overall fields in the axial direction as they traverse the Time of Flight mass analyser in order to achieve the highest possible resolution.

[0293] If ions are simply injected into a pair of coaxial cylinders through a small hole without scanning the internal field then no stable trajectories are achieved and the injected ions will always describe a trajectory that ends up outside the space between the concentric cylinders. Two examples of such trajectories are shown in FIGS. 22A and 22B.

[0294] In FIG. 22A an ion is injected at an energy such that it would describe a circular trajectory halfway between the inner and outer cylinders if it were to find itself instantaneous created at such a position and with its velocity component entirely tangential to both cylinders. It can be seen that this ion is completely unstable quickly striking the inner cylinder after only about a quarter of one revolution.

[0295] In FIG. 22B the ion is injected at higher energy and is still unstable although it survives for about one and a half revolutions before it strikes the outer cylinder.

[0296] So it is desirable to find a way to inject ions into the instrument such that the fill factor is minimised and with little or no mass dependence on radial position within the device once the ions are in stable orbits.

[0297] The segmented coaxial cylinder geometry which is utilised according to the preferred embodiment enables different voltages to be applied to different segments and different portions of such segments as required. According to the preferred embodiment the acceleration region of the Time of Flight analyser is divided into two sectors. This allows control of the radial confining field with respect to sector angle and time. By pulsing the voltage to an angular portion of either the inner or outer cylinder the confining radial field may be pulsed ON or OFF.

[0298] FIG. 23A shows how in a preferred embodiment the device is split into two regions or sectors. With reference to the dials of a clock face the first region or sector (which extends from 12:00 o'clock around to 3:00 o'clock) is separated from the rest of the electrodes (which extend from 3:00 o'clock clockwise around to 12:00 o'clock).

[0299] FIG. 23A shows lines of equipotential and shows how ions that are injected at the top of the device from the right will experience a substantially field free flight in the first sector before they are deflected into the main radial sector in an anticlockwise direction. As the field is essentially static at this point mono energetic ions of differing mass take the same trajectory. This will be understood by those skilled in the art since this is a fundamental principle of electrostatics.

[0300] Whilst the ions are traversing around the main sector the small sector may be switched up to the same voltage as the main sector such that a continuous radial trapping field is created by the time the ions complete the circuit (see FIG. 23B). Such a scheme allows ion packets that are relatively long temporally to be injected into the device giving the Time of Flight mass analyser a high duty cycle of operation.

[0301] The preferred embodiment is therefore particularly advantageous in that it enables ions to be injected into the instrument such that the fill factor is minimised and with effectively zero mass dependence on radial position within the device once the ions are in stable orbits.

[0302] One of the problems with known multipass Time of Flight mass analysers is that it is difficult to determine the number of passes that a particular species of ion has traversed when detected. It is known to seek to address this problem by injecting a limited mass range into the mass analyser so that such aliasing is impossible. If a shorter temporal packet of ions is injected into the analyser then it may be possible to determine the mass by retaining the angular position of the ion packet when it strikes the detector.

[0303] With reference to FIGS. 24A-B three ions M1, M2, and M3 (where M1>M2>M3) may be injected into the mass analyser in a compact temporal packet. Immediately after injection in FIG. 24A it can be seen that the different masses have begun to separate rotationally. With a detector that retains angular information it is possible to predict the change in angle as each of the ions traverse the analyser. The combination of time of flight and angular position is enough to unequivocally determine the mass to charge (and therefore the number of roundtrips of the analyser) in certain cases. This extra angular information allows larger mass ranges to be injected into the analyser at any one time, so reducing the number of different spectra to be stitched together to cover the entire mass range.

[0304] Although the present invention has been described with reference to preferred embodiments, it will be understood by those skilled in the art that various changes in form and detail may be made without departing from the scope of the invention as set forth in the accompanying claims.